SAFRAN S.A.

France

Back to Profile

1-98 of 98 for SAFRAN S.A. and 1 subsidiary Sort by
Query
Patent
Canada - CIPO
Excluding Subsidiaries
Aggregations Reset Report
Owner / Subsidiary
[Owner] SAFRAN S.A. 98
SNECMA S.A. 7
Date
2023 2
2022 5
2021 2
2020 9
2019 13
See more
IPC Class
F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion 17
F01D 5/18 - Hollow blades; Heating, heat-insulating, or cooling means on blades 8
C23C 28/00 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and 7
B22C 9/04 - Use of lost patterns 6
B22C 9/10 - Cores; Manufacture or installation of cores 6
See more
Status
Pending 61
Registered / In Force 37
Found results for  patents

1.

METHOD AND SYSTEM FOR DETERMINING THE PRESSURE OF AN AIRCRAFT TYRE

      
Document Number 03233188
Status Pending
Filing Date 2022-10-19
Open to Public Date 2023-04-27
Owner
  • COMPAGNIE GENERALE DES ETABLISSEMENTS MICHELIN (France)
  • SAFRAN (France)
  • SAFRAN ELECTRONICS & DEFENSE (France)
  • SAFRAN LANDING SYSTEMS (France)
Inventor Neba, Eric Carin

Abstract

The invention relates to a method and a system for determining the temperature in a mounted aircraft tyre. The system is characterized in that it comprises two temperature sensors installed inside the tyre.

IPC Classes  ?

  • B60C 23/04 - Signalling devices actuated by tyre pressure mounted on the wheel or tyre
  • B64F 5/60 - Testing or inspecting aircraft components or systems
  • B64C 25/36 - Arrangements or adaptations of wheels, tyres or axles in general
  • G01K 1/02 - Means for indicating or recording specially adapted for thermometers
  • G01K 3/06 - Thermometers giving results other than momentary value of temperature giving integrated values in respect of space
  • G01L 11/00 - Measuring steady or quasi-steady pressure of a fluid or a fluent solid material by means not provided for in group or
  • G01L 17/00 - Devices or apparatus for measuring tyre pressure or the pressure in other inflated bodies

2.

MACHINERY FOR WINDING A FIBROUS TEXTURED MATERIAL, AND ASSOCIATED WINDING METHOD

      
Document Number 03230788
Status Pending
Filing Date 2022-08-25
Open to Public Date 2023-03-09
Owner
  • SAFRAN (France)
  • SAFRAN LANDING SYSTEMS (France)
Inventor
  • Leclercq, Sylvain Didier
  • Roirand, Quentin
  • Coupe, Dominique Marie Christian
  • Chauvin, Thierry Patrick
  • Tran, Nicolas

Abstract

The present invention relates to machinery (10) for winding a fibrous textured material (12, 120, 220) about a support (14, 140, 240), allowing the gradual modification of the shape of the support as the winding progresses, and comprising compaction devices (20,329) for the purpose of reducing the wrinkling of the textured material obtained after compaction.

IPC Classes  ?

  • B29B 11/16 - Making preforms characterised by structure or composition comprising fillers or reinforcements
  • F16C 7/02 - Constructions of connecting-rods with constant length

3.

METHOD FOR PRODUCING TURBOMACHINE DISCS

      
Document Number 03220785
Status Pending
Filing Date 2022-06-09
Open to Public Date 2022-12-15
Owner
  • SAFRAN (France)
  • AUBERT & DUVAL (France)
Inventor
  • Delfosse, Jerome
  • Franchet, Jean-Michel Patrick Maurice

Abstract

The present disclosure relates to a method for manufacturing discs for turbomachines, the method comprising: obtaining a nickel-based alloy powder; shaping the powder in order to obtain a disc; characterised in that the step of obtaining a powder comprises: atomising a nickel-based alloy by electrode induction gas atomisation (EIGA) from a nickel-based alloy electrode, resulting in a raw powder; and sieving the raw powder under an inert atmosphere or under a vacuum to a particle size of between 150 µm and 50 µm, for example 125 µm or 75 µm, resulting in the nickel-based alloy powder.

IPC Classes  ?

  • B22F 1/05 - Metallic powder characterised by the size or surface area of the particles

4.

SYSTEM AND METHOD FOR COLD WORKING A METAL SURFACE

      
Document Number 03116745
Status Pending
Filing Date 2021-04-30
Open to Public Date 2022-10-30
Owner SAFRAN (France)
Inventor
  • Badreddine, Jawad
  • Levesque, Martin
  • Miao, Hong-Yan
  • Caya, Marie-Christine
  • Racine, Sylvain
  • Bousquet-Jette, Christopher

Abstract

Système d'écrouissage (10) d'une surface d'une pièce métallique comprenant un support de la pièce métallique, un bras articulé robotisé (14) portant un dispositif d'écrouissage (16) de la pièce métallique, un dispositif de mesure de la température (20) sur la surface de la pièce métallique, un dispositif de création d'un champ thermique dans la pièce métallique comprenant un dispositif de chauffe localisée à distance de la pièce métallique, le dispositif de création du champ thermique étant configure pour fonctionner en même temps que le dispositif de mesure de la température et le dispositif d'écrouissage. Procédé d'écrouissage d'une surface d'une pièce métallique au moyen du système d'écrouissage (10)

IPC Classes  ?

  • B23P 9/02 - Treating or finishing by applying pressure, e.g. knurling
  • C21D 1/18 - Hardening; Quenching with or without subsequent tempering
  • C21D 1/54 - Determining when the hardening temperature has been reached by measurement of magnetic or electrical properties
  • C21D 7/06 - Modifying the physical properties of iron or steel by deformation by cold working of the surface by shot-peening or the like
  • C21D 11/00 - Process control or regulation for heat treatments

5.

METHOD FOR STOPPING A GAS TURBINE ENGINE OF A TURBOGENERATOR FOR AIRCRAFT

      
Document Number 03200639
Status Pending
Filing Date 2021-12-01
Open to Public Date 2022-06-09
Owner
  • SAFRAN (France)
  • SAFRAN HELICOPTER ENGINES (France)
  • SAFRAN POWER UNITS (France)
Inventor
  • Mercier-Calvairac, Fabien
  • Parmentier, Nicolas Claude
  • Real, Denis Antoine Julien

Abstract

This method for stopping at least one aircraft turbogenerator (1) comprises: - controlling the stopping (E1) of the turbogenerator (1); - passing from the nominal operating speed (Nref) of the power shaft (3, 12) to a first operating speed (N1) lower than the nominal speed (Nref), for a first predetermined duration (t2); - controlling the extinction of the combustion chamber (6) of the gas turbine (2); - maintaining the rotation of the gas turbine at a second speed (N2) for a second predetermined duration (t3), the power shaft (3, 12) being at a second speed (N2) lower than the first operating speed (N1) and, - controlling the stopping of the reversible electric machine (7) in order to no longer drive the power shaft (3, 12), in order to cause a progressive stopping (E9, E10) of the rotation of the gas turbine (2).

IPC Classes  ?

  • F01D 15/10 - Adaptations for driving, or combinations with, electric generators

6.

FAIL-SAFE GUIDE DEVICE

      
Document Number 03199890
Status Pending
Filing Date 2021-11-15
Open to Public Date 2022-06-02
Owner
  • SAFRAN (France)
  • SAFRAN ELECTRONICS & DEFENSE (France)
Inventor
  • Lawniczak, Remi-Louis
  • Laurensan, Frederic
  • Cartry, Thierry
  • Betbeder-Lauque, Xavier

Abstract

The invention relates to a device comprising: - a mount (10), - a frame (20) mounted so as to rotate relative to the mount; - a control arm (40) mounted so as to rotate on the frame (20); a roll spider (80) mounted so as to rotate on the frame (20); - a pitch spider (100) mounted so as to rotate on the control arm (40); - a roll motor (120) which is fixed relative to the frame (20) and which comprises a roll shaft (121) mounted so as to rotate on the roll spider (80); - a pitch motor (140) which is fixed relative to the frame (20) and which comprises a pitch shaft (141) mounted so as to rotate on the pitch spider (100). Drawing_references_to_be_translated

IPC Classes  ?

  • F16C 35/067 - Fixing them in a housing
  • B64C 13/04 - Initiating means actuated personally
  • F16C 35/02 - Rigid support of bearing units; Housings, e.g. caps, covers in the case of sliding-contact bearings
  • G05G 9/047 - Manually-actuated control mechanisms provided with one single controlling member co-operating with two or more controlled members, e.g. selectively, simultaneously the controlling member being movable in different independent ways, movement in each individual way actuating one controlled member only in which movement in two or more ways can occur simultaneously the controlling member being movable by hand about orthogonal axes, e.g. joysticks

7.

METHOD FOR DETERMINING AN EFFICIENCY FAULT OF AN AIRCRAFT TURBOSHAFT ENGINE MODULE

      
Document Number 03196672
Status Pending
Filing Date 2021-10-28
Open to Public Date 2022-05-12
Owner
  • SAFRAN (France)
  • SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Razakarivony, Sebastien Philippe
  • Favre, Christophe
  • Joseph, Julien
  • Lamouroux, Jean

Abstract

The invention relates to a method for determining an efficiency fault (R11-R15) of at least one module (11-15) of a turboshaft engine (T) of an aircraft (A), the method for determining comprising: ? A step of determining an estimated real mapping (CARE), ? A step of determining real indicators (IRE) from the estimated real mapping (CARE), ? A step of determining (E3) a plurality of simulated mappings from a simulation of a theoretical model of the turboshaft engine (T) for different efficiency configurations, ? A step of determining (E4) simulated indicators (ISx) for each simulated mapping (CARSx), ? A step of training (E5) a mathematical model (CLASS) by coupling the simulated indicators (ISx) with efficiency configurations (CR), and ? A step of applying (E6) said mathematical model (CLASS) to the real indicators (IRE) so as to deduce therefrom a real efficiency configuration (CR).

IPC Classes  ?

  • F02C 9/00 - Controlling gas-turbine plants; Controlling fuel supply in air-breathing jet-propulsion plants
  • G05B 23/02 - Electric testing or monitoring

8.

ACOUSTIC PANEL AND ASSOCIATED MANUFACTURING METHOD

      
Document Number 03084631
Status Pending
Filing Date 2020-06-23
Open to Public Date 2021-12-23
Owner SAFRAN (France)
Inventor
  • Therriault, Daniel
  • Iervolino, Filippo
  • Pierre, Juliette
  • Piccirelli, Nicola
  • Ross, Annie
  • Costa Baptista, Josue

Abstract

Panneau acoustique comprenant deux peaux (2, 3) sensiblement parallèles entre lesquelles sont disposées des cavités formant des résonateurs de Helmholtz, l'une desdites peaux (2, 3) étant percées d'orifices (8a, 8b, 9) débouchant chacun dans une desdites cavités et formant un col des résonateurs, caractérisé en ce qu'une ou plusieurs desdites cavités sont formées par une structure (4) creuse en forme de prisme droit à base tri angulaire.

IPC Classes  ?

  • B32B 3/12 - Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially having particular features of form characterised by a discontinuous layer, i.e. apertured or formed of separate pieces of material characterised by a layer of regularly-arranged cells whether integral or formed individually or by conjunction of separate strips, e.g. honeycomb structure
  • B32B 3/24 - Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially having particular features of form characterised by a discontinuous layer, i.e. apertured or formed of separate pieces of material characterised by an apertured layer, e.g. of expanded metal
  • B32B 27/08 - Layered products essentially comprising synthetic resin as the main or only constituent of a layer next to another layer of a specific substance of synthetic resin of a different kind
  • B32B 37/14 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the properties of the layers
  • E04B 1/86 - Sound-absorbing elements slab-shaped

9.

COMPOSITION FOR ADDITIVE MANUFACTURING

      
Document Number 03078975
Status Pending
Filing Date 2020-04-21
Open to Public Date 2021-10-21
Owner SAFRAN (France)
Inventor
  • Piccirelli, Nicola
  • Therriault, Daniel
  • Otera Navas, Ivonne
  • Diouf Lewis, Audrey
  • Iervolino, Filippo
  • Abderrafai, Yahya

Abstract

L'invention concerne une composition pour fabrication additive caractérisée en ce qu'elle comprend : - un mélange polymérique comprenant une polyétheréthercétone et un polyétherimide, et - des fibres de carbone.

IPC Classes  ?

  • C08L 71/10 - Polyethers derived from hydroxy compounds or from their metallic derivatives from phenols
  • B29C 64/165 - Processes of additive manufacturing using a combination of solid and fluid materials, e.g. a powder selectively bound by a liquid binder, catalyst, inhibitor or energy absorber
  • C08K 3/013 - Fillers, pigments or reinforcing additives
  • B33Y 70/10 - Composites of different types of material, e.g. mixtures of ceramics and polymers or mixtures of metals and biomaterials
  • C08K 3/04 - Carbon
  • C08K 7/06 - Elements
  • C08L 79/08 - Polyimides; Polyester-imides; Polyamide-imides; Polyamide acids or similar polyimide precursors

10.

PROCESS FOR SHAPING A LAYER OF ALUMINA ON THE SURFACE OF A METALLIC SUBSTRATE

      
Document Number 03043564
Status Pending
Filing Date 2019-05-15
Open to Public Date 2020-11-15
Owner SAFRAN (France)
Inventor
  • Cavarroc, Marjorie Christine
  • Knittel, Stephane
  • Sapieha, Jolenta
  • Martinu, Ludvik
  • Bergeron, Florence
  • Loquai, Simon

Abstract

L'invention concerne un procédé de formation d'une couche d'alumine (203) à la surface d'un substrat métallique (201) en alliage comprenant de l'aluminium, le procédé comprenant au moins : - le dépôt d'une première couche d'aluminium sur une surface du substrat métallique, - le dépôt d'une deuxième couche par dépôt en phase vapeur sur la première couche, la deuxième couche comprenant de l'aluminium, un halogène et de l'oxygène, et - le traitement thermique du substrat revêtu des première et deuxième couches sous atmosphère oxydante afin de former la couche d'alumine à la surface du substrat métallique.

IPC Classes  ?

  • C23C 28/00 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and
  • C23C 14/58 - After-treatment
  • C23C 16/56 - After-treatment

11.

TURBOMACHINE BLADE WITH IMPROVED COOLING

      
Document Number 03138077
Status Pending
Filing Date 2020-04-24
Open to Public Date 2020-11-12
Owner
  • SAFRAN (France)
  • SAFRAN AIRCRAFT ENGINES (France)
Inventor
  • Ostino, Leandre
  • Auzillon, Pierre Guillaume
  • Slusarz, Michel
  • Eneau, Patrice
  • De Rocquigny, Thomas Olivier Michel Pierre
  • Cariou, Romain Pierre
  • Tang, Ba-Phuc
  • Rollinger, Adrien Bernard Vincent
  • Simon, Vianney

Abstract

The invention relates to a turbine vane comprising a root carrying a blade terminated by a tip in the form of a squealer tip, the blade having an intrados wall and an extrados wall, as well as a leading edge, a trailing edge, and a tip wall delimiting a bottom of the squealer tip, by which the intrados wall is connected to the extrados wall, said blade also comprising: - a serpentine median circuit (28), including a first radial pipe (41) that collects air at the root and is connected by a first bend (46) to a second radial pipe (42) that is connected by a second bend (47) to a third radial pipe (43); - a cavity (36) under the squealer tip running along the extrados wall (21) and extending from a central region of the tip (S) to the trailing edge (17); - a central radial pipe (34) collecting air at the root and extending between at least two of the three pipes (41, 42, 43) of the median circuit (28) and directly supplying the cavity (36) under the squealer tip.

IPC Classes  ?

  • F01D 5/18 - Hollow blades; Heating, heat-insulating, or cooling means on blades
  • B22C 9/10 - Cores; Manufacture or installation of cores
  • B22C 9/24 - Moulds for peculiarly-shaped castings for hollow articles

12.

EXTRUDER HEAD FOR ADDITIVE MANUFACTURING, SYSTEM AND PROCESS FOR ADDITIVE MANUFACTURING

      
Document Number 03041017
Status Pending
Filing Date 2019-04-23
Open to Public Date 2020-10-23
Owner SAFRAN (France)
Inventor
  • Lafrance, Thierry
  • Therriault, Daniel
  • Bazin, Benoit
  • Piccirelli, Nicola
  • Trudeau Lalonde, Francis

Abstract

Une tête d'extrusion (100) pour fabrication additive comprend une enceinte (110) délimitant une chambre d'alimentation (140). L'enceinte comporte au moins un port d'entrée (120) débouchant dans la chambre d'alimentation (140) et configuré pour recevoir un matériau à extruder sous pression et une pluralité de buses d'extrusion (160). Chaque buse est en communication avec la chambre d'alimentation (140) et débouche à l'extérieur de l'enceinte via un orifice de sortie. Les buses de la pluralité de buses sont disposées adjacentes les unes par rapport aux autres avec un espacement déterminé entre chaque orifice de sortie de buse.

IPC Classes  ?

  • B29C 64/209 - Heads; Nozzles
  • B33Y 10/00 - Processes of additive manufacturing
  • B33Y 30/00 - ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING - Details thereof or accessories therefor
  • B29C 64/106 - Processes of additive manufacturing using only liquids or viscous materials, e.g. depositing a continuous bead of viscous material

13.

SYSTEM FOR MONITORING THE HEALTH OF A HELICOPTER

      
Document Number 03135956
Status Pending
Filing Date 2020-04-17
Open to Public Date 2020-10-22
Owner
  • SAFRAN (France)
  • SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Razakarivony, Sebastien Philippe
  • Favre, Christophe
  • Joseph, Julien
  • Lamouroux, Jean

Abstract

The invention relates to a system for monitoring the health of a helicopter, comprising a helicopter and a device for determining a change in state of the engine that is configured to collect data measured by engine sensors and external conditions during a stable flight phase and to process said measured data in the following way: comparing said measured data with a reference model of the engine, determining, at each time interval, an instantaneous discrepancy between each item of data measured and each item of data estimated by the reference model of the engine, determining, throughout the stable flight phase, an overall discrepancy between the measured data and the data estimated by the reference model of the engine, determining, at each time interval of the stable flight phase, an intrinsic residual corresponding to a difference between the instantaneous discrepancy and the overall discrepancy, determining a deviating portion corresponding to the part of the intrinsic residual that does not satisfy a predetermined criterion, each deviating portion containing an item of information relating to a pilot action that is not recorded, and determining a corrected residual corresponding to the instantaneous discrepancy from which the deviating portion has been subtracted, the corrected residual being analysed in order to determine whether the state of the engine has changed.

IPC Classes  ?

  • G01M 15/00 - Testing of engines
  • B64F 5/60 - Testing or inspecting aircraft components or systems

14.

TURBINE ENGINE VANE EQUIPPED WITH A COOLING CIRCUIT AND LOST-WAX METHOD FOR MANUFACTURING SUCH A VANE

      
Document Number 03133761
Status Pending
Filing Date 2020-03-16
Open to Public Date 2020-10-01
Owner
  • SAFRAN (France)
  • SAFRAN AIRCRAFT ENGINES (France)
Inventor
  • Cariou, Romain Pierre
  • Pelleterat De Borde, Myriam
  • Simon, Vianney
  • Rollinger, Adrien Bernard Vincent

Abstract

The invention relates to a turbine engine vane (20) comprising a blade (21) extending along a radial axis and a first cooling circuit (28) arranged inside the blade, the first cooling circuit (28) comprising a first cavity (34) and a second cavity (35) disposed downstream of the first cavity in a direction of circulation of a coolant in the blade, the first and second cavities radially extending inside the blade and being at least partly separated by a first radial partition (36) having a radially internal free end (37), which at least partly demarcates a first coolant passage (40) connecting the first and second cavities. According to the invention, the radially internal free end (37) is enlarged by having a general transverse section substantially in the form of a keyhole.

IPC Classes  ?

  • F01D 5/18 - Hollow blades; Heating, heat-insulating, or cooling means on blades

15.

TURBINE ENGINE VANE PROVIDED WITH AN OPTIMIZED COOLING CIRCUIT

      
Document Number 03133762
Status Pending
Filing Date 2020-03-16
Open to Public Date 2020-10-01
Owner
  • SAFRAN AIRCRAFT ENGINES (France)
  • SAFRAN (France)
Inventor
  • Fanelli, Jeremy Jacques Attilio
  • Cariou, Romain Pierre
  • Simon, Vianney
  • Tang, Ba-Phuc

Abstract

The invention relates to a turbine engine blade (20) comprising: - an airfoil (21) with a pressure-side wall and a suction-side wall which are connected upstream by a leading edge (26) and downstream by a trailing edge (27), - a cooling circuit (28) which comprises an internal cavity extending inside the airfoil and a plurality of outlet openings each oriented substantially along a longitudinal axis X, each outlet opening communicating with the cavity and being arranged in the vicinity of the trailing edge, and - a calibration device (33) arranged in the cavity and provided with calibration conduits (34) which are arranged substantially opposite the outlet openings. According to the invention, the calibration conduits (34) each comprise an oblong transverse section which is substantially perpendicular to the longitudinal axis.

IPC Classes  ?

  • F01D 5/18 - Hollow blades; Heating, heat-insulating, or cooling means on blades

16.

PROPULSION SYSTEM FOR AN AIRCRAFT

      
Document Number 03123828
Status Pending
Filing Date 2019-12-20
Open to Public Date 2020-06-25
Owner
  • SAFRAN (France)
  • SAFRAN AIRCRAFT ENGINES (France)
  • SAFRAN NACELLES (France)
Inventor
  • Besse, Jean-Louis Robert Guy
  • Maldonado, Ye-Bonne Karina

Abstract

The invention relates to a propulsion system (100) for an aircraft, comprising at least one rotor (110) and a nacelle cowling (120) extending around the at least one rotor (110), said nacelle cowling (120) being sectored and comprising at least one sector (130a, 130b) which is fixed and sectors (141a, 141b, 142a, 142b) which are retractable in the peripheral direction (F1, F2) relative to an axis of rotation (X) of the rotor (110), characterised in that the retractable sectors (141a, 141b, 142a, 142b) comprise at least a first series of sectors (141a, 142a) which are telescopically retractable in or on at least one fixed sector (130a) and at least a second series of sectors (141b, 142b) which are telescopically retractable in or on at least one fixed sector (130b), the at least one fixed sector (130a, 130b) having an angular extent around the axis (X) which is less than or equal to 90°.

IPC Classes  ?

  • B64C 11/00 - Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
  • B64D 29/06 - Attaching of nacelles, fairings, or cowlings

17.

ENCASED PRESSURE SENSOR

      
Document Number 03111048
Status In Force
Filing Date 2019-08-27
Open to Public Date 2020-03-05
Grant Date 2021-12-14
Owner
  • SAFRAN ELECTRONICS & DEFENSE (France)
  • COMPAGNIE GENERALE DES ETABLISSEMENTS MICHELIN (France)
  • SAFRAN (France)
  • SAFRAN LANDING SYSTEMS (France)
Inventor
  • Riou, Jean-Christophe
  • Bailly, Eric

Abstract

Pressure measurement device (1) comprising a case (20) extending around an electronic card (30) provided with a pressure sensor (40), - the case (20) delimiting with a first face (31) of the electronic card (30) a first leaktight volume (3); - the case (20) also delimiting with a second face (32) of the electronic card (30) opposite to the first face (31) a second leaktight volume (4); - the case (20) comprising at least one first channel (24) placing in fluidic communication the exterior medium (5) outside the case (20) and the first leaktight volume (3); - the electronic card (30) comprising at least one second channel (33) placing in fluidic communication the first volume (3) and the second volume (4); - the link between the case (20) and the electronic card (30) being designed to permit a relative motion of the case (20) and of the electronic card.

IPC Classes  ?

  • G01L 17/00 - Devices or apparatus for measuring tyre pressure or the pressure in other inflated bodies
  • B60C 23/04 - Signalling devices actuated by tyre pressure mounted on the wheel or tyre
  • G01L 19/04 - Means for compensating for effects of changes of temperature
  • G01L 19/06 - Means for preventing overload or deleterious influence of the measured medium on the measuring device or vice versa
  • G01L 19/14 - Housings

18.

NICKEL-BASED SUPERALLOY FOR MANUFACTURING A PART BY POWDER FORMING

      
Document Number 03107198
Status Pending
Filing Date 2019-07-24
Open to Public Date 2020-02-06
Owner SAFRAN (France)
Inventor
  • Richard, Sebastien Jean
  • Rame, Jeremy
  • Menou, Edern

Abstract

The invention relates to a nickel-based superalloy containing, in weight percentages: - 5 to 6.5% of aluminum, - 4.5 to 7% of cobalt, - 14.5 to 16.5% of chrome, - 0 to 0.2% of hafnium, - 0 to 1.5% of molybdenum, - 2 to 3.5% of tantalum, - 0 to 2% of titanium, - 1 to 2.5% of tungsten, - 0 to 0.08% of zirconium, - 0 to 0.03% of boron and - 0 to 0.07% of carbon, the remainder being nickel and inevitable impurities.

IPC Classes  ?

  • C22C 19/05 - Alloys based on nickel or cobalt based on nickel with chromium

19.

METHOD FOR PRODUCING A METAL BLADED ELEMENT FOR A TURBOMACHINE OF AN AIRCRAFT

      
Document Number 03097078
Status Pending
Filing Date 2019-04-19
Open to Public Date 2019-10-24
Owner
  • SAFRAN AIRCRAFT ENGINES (France)
  • SAFRAN (France)
Inventor
  • Soisson, Marc
  • Boukerma, Said
  • Lisowski, Janusz
  • Gimel, Alexandre
  • Saboundji, Amar

Abstract

The invention relates to a method for producing a metal bladed element for a turbomachine of an aircraft, said bladed element comprising at least one blade having a lower surface and an upper surface extending between a leading edge and a trailing edge of the blade, the trailing edge having to have a thickness X1, said method comprising the steps of: a) producing the bladed element by lost-wax casting, and b) finishing the bladed element, characterised in that step b) comprises the chemical milling at least of the trailing edge of the or each blade so as to obtain said thickness X1 which cannot be directly obtained by step a).

IPC Classes  ?

  • C23F 1/04 - Chemical milling
  • B23P 15/02 - Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from one piece
  • F01D 5/00 - Blades; Blade-carrying members; Heating, heat-insulating, cooling, or antivibration means on the blades or the members
  • F01D 7/00 - Rotors with blades adjustable in operation; Control thereof
  • G01M 1/34 - Compensating unbalance by removing material from the body to be tested, e.g. from the tread of tyres

20.

CORE FOR METAL CASTING AN AERONAUTICAL PART

      
Document Number 03097010
Status Pending
Filing Date 2019-04-12
Open to Public Date 2019-10-17
Owner SAFRAN (France)
Inventor
  • Rollinger, Adrien Bernard Vincent
  • Bohli, Ramzi
  • Niane, Ngadia Taha
  • Le Hegarat, Alain
  • Cariou, Romain Pierre
  • Grange, David
  • Guerche, Didier Maurice Marceau

Abstract

The present invention relates to a core for metal casting an aeronautical part such as a turbine blade, the core being designed for arrangement in an inner cavity defined by a mould, the core comprising: a body (13) intended to form the inner shape of the turbine blade; and an impact portion (15), disposed along at least a portion of the periphery of the body (13) in such a way as to break up a fluid jet when the inner receptacle is filled with fluid, the impact portion (15) having a apex (17) and at least one deflecting wall (19) converging towards the apex (17).

IPC Classes  ?

  • B22C 9/10 - Cores; Manufacture or installation of cores

21.

NICKEL-BASED SUPERALLOY, SINGLE-CRYSTAL BLADE AND TURBOMACHINE

      
Document Number 03081885
Status Pending
Filing Date 2018-11-14
Open to Public Date 2019-05-23
Owner
  • SAFRAN (France)
  • OFFICE NATIONAL D'ETUDES ET DE RECHERCHES AEROSPATIALES (France)
Inventor
  • Rame, Jeremy
  • Jaquet, Virginie
  • Delautre, Joel
  • Guedou, Jean-Yves
  • Caron, Pierre
  • Lavigne, Odile
  • Locq, Didier
  • Perrut, Mikael

Abstract

The invention relates to a nickel-based superalloy comprising, in weight percentages, 4.0 to 5.5 % rhenium, 3.5 to 12.5 % cobalt, 0.30 to 1.50 % molybdenum, 3.5 to 5.5 % chromium, 3.5 to 5.5 % tungsten, 4.5 to 6.0 % aluminum, 0.35 to 1.50 % titanium, 8.0 to 10.5 % de tantalum, 0.15 to 0.30 % hafnium, 0.05 to 0.15 % silicon, the remainder being nickel and inevitable impurities. The invention also relates to a single-crystal blade (20A, 20B) comprising such an alloy and to a turbomachine (10) comprising such a blade (20A, 20B).

IPC Classes  ?

  • C22C 19/05 - Alloys based on nickel or cobalt based on nickel with chromium
  • F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion

22.

NICKEL-BASED SUPERALLOY, SINGLE-CRYSTAL BLADE AND TURBOMACHINE

      
Document Number 03081896
Status Pending
Filing Date 2018-11-14
Open to Public Date 2019-05-23
Owner
  • SAFRAN (France)
  • OFFICE NATIONAL D'ETUDES ET DE RECHERCHES AEROSPATIALES (France)
Inventor
  • Rame, Jeremy
  • Jaquet, Virginie
  • Delautre, Joel
  • Guedou, Jean-Yves
  • Caron, Pierre
  • Lavigne, Odile
  • Locq, Didier
  • Perrut, Mikael

Abstract

The invention relates to a nickel-based superalloy comprising, in weight percentages, 4.0 to 5.5 % rhenium, 1.0 to 3.0 ruthenium, 2.0 to 14.0 % cobalt, 0.3 to 1.0 % molybdenum, 3.0 to 5.0 % chromium, 2.5 to 4.0 % tungsten, 4.5 to 6.5 % aluminium, 0.50 to 1.50 % titanium, 8.0 to 9.0 % de tantalum, 0.15 to 0.30 % hafnium, 0.05 to 0.15 % silicon, the rest being nickel and inevitable impurities. The invention also relates to a single-crystal blade (20A, 20B) comprising such an alloy and to a turbomachine (10) comprising such a blade (20A, 20B).

IPC Classes  ?

  • C22C 19/05 - Alloys based on nickel or cobalt based on nickel with chromium
  • F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion

23.

PARAMETER MEASUREMENT SYSTEM FOR A MOUNTED ASSEMBLY

      
Document Number 03080080
Status Pending
Filing Date 2018-10-26
Open to Public Date 2019-05-02
Owner
  • COMPAGNIE GENERALE DES ETABLISSEMENTS MICHELIN (France)
  • SAFRAN (France)
  • SAFRAN LANDING SYSTEMS (France)
  • SAFRAN ELECTRONICS & DEFENSE (France)
Inventor
  • Fagot-Revurat, Lionel
  • Destraves, Julien

Abstract

The invention relates to a parameter measurement system for a mounted assembly comprising an electronic device for measuring the parameters of the mounted assembly and a connecting interface made of elastomeric material including the electronic device. The electronic measurement device comprises: - a UHF radiofrequency antenna; - an electronic card with an electronic chip coupled to the UHF radiofrequency antenna, a sensor for measuring the parameter of the mounted assembly, a microcontroller and an electrical circuit. The measurement system is characterised in that it comprises a ground plane connected to the electronic card, in that the electronic card comprises an energy manager and a capacitive element, in that the coupling between the electronic chip and the UHF radiofrequency antenna is an electrical coupling and in that the electronic chip, the microcontroller and the measurement sensor are components with low energy consumption.

IPC Classes  ?

  • H01Q 1/22 - Supports; Mounting means by structural association with other equipment or articles

24.

PART COMPRISING A PROTECTIVE COATING HAVING A GRADUAL COMPOSITION

      
Document Number 03079979
Status Pending
Filing Date 2018-10-26
Open to Public Date 2019-05-02
Owner SAFRAN (France)
Inventor
  • Bianchi, Luc
  • Sallot, Pierre

Abstract

The invention relates to a part made from a composite material having a ceramic matrix and comprising a protection device, the protection comprising a coating layer having a gradual composition. The aforementioned gradual-composition coating layer comprises at least one silicon phase and one aluminium phase, the proportions of which change according to the height in the layer, with a first height in the gradual-composition coating layer corresponding to a silicon-free composition, and a second height corresponding to an aluminium-free composition. The invention also relates to a method for producing such a protection, and to a device for carrying out the method.

IPC Classes  ?

  • C23C 4/134 - Plasma spraying
  • C23C 4/129 - Flame spraying
  • C23C 4/10 - Oxides, borides, carbides, nitrides or silicides; Mixtures thereof
  • C23C 28/04 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and only coatings of inorganic non-metallic material

25.

METHOD FOR DETERMINING A RECOMMENDED INFLATION PRESSURE FOR AN AIRCRAFT TYRE, AND ASSOCIATED MAINTENANCE METHODS

      
Document Number 03078169
Status Pending
Filing Date 2018-10-26
Open to Public Date 2019-05-02
Owner
  • COMPAGNIE GENERALE DES ETABLISSEMENTS MICHELIN (France)
  • SAFRAN (France)
  • SAFRAN LANDING SYSTEMS (France)
  • SAFRAN ELECTRONICS & DEFENSE (France)
Inventor
  • Arnoux, Michael
  • Neba, Eric Carin

Abstract

The invention relates to a method for determining an expected inflation pressure in an aircraft tyre that is equipped with a pressure and temperature sensor. The invention also relates to an assisted maintenance method for an aircraft tyre, as well as to a portable electronic device designed to assist with maintenance.

IPC Classes  ?

  • B60C 23/04 - Signalling devices actuated by tyre pressure mounted on the wheel or tyre
  • B60C 23/20 - Devices for measuring or signalling tyre temperature

26.

TURBINE COMPONENT MADE FROM SUPERALLOY COMPRISING RHENIUM AND ASSOCIATED MANUFACTURING PROCESS

      
Document Number 03081099
Status Pending
Filing Date 2018-10-17
Open to Public Date 2019-04-25
Owner SAFRAN (France)
Inventor
  • Saboundji, Amar
  • Jaquet, Virginie

Abstract

The invention relates to a turbine component comprising a substrate made from monocrystalline nickel-based superalloy comprising rhenium, which has a ?-?' Ni phase, and an average weight fraction of chromium of less than 0.08, a sublayer made from nickel-based metal superalloy covering the substrate, characterized in that the sublayer made from metal superalloy comprises at least aluminium, nickel, chromium, silicon, hafnium and has, predominantly by volume, a ?'-Ni 3 Al phase. Figure 4

IPC Classes  ?

  • F01D 5/00 - Blades; Blade-carrying members; Heating, heat-insulating, cooling, or antivibration means on the blades or the members
  • F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups

27.

COMPONENT PROTECTED BY AN ENVIRONMENTAL BARRIER

      
Document Number 03077640
Status Pending
Filing Date 2018-10-03
Open to Public Date 2019-04-11
Owner SAFRAN (France)
Inventor
  • Bianchi, Luc
  • Joubert, Hugues Denis
  • Picot, Philippe
  • Saboundji, Amar

Abstract

The invention concerns a component (10) comprising: a substrate (20) of which at least one part adjacent to a surface (S) of the substrate is made from a material comprising silicon; a bonding sublayer (30) situated on the surface (S) of the substrate and comprising silicon, an environmental barrier (40) that comprises an outer layer (42) made from ceramic covering the bonding sublayer (30), characterised in that said environmental barrier (40) additionally comprises a self-healing inner layer (41) situated between the bonding sublayer (30) and the outer layer (42), said inner layer (41) comprising a matrix in which silica-forming particles are dispersed, these particles being capable of generating a crack-healing phase in the matrix in the presence of oxygen.

IPC Classes  ?

  • C04B 41/89 - Coating or impregnating for obtaining at least two superposed coatings having different compositions
  • C23C 4/11 - Oxides
  • C04B 41/90 - Coating or impregnating for obtaining at least two superposed coatings having different compositions at least one coating being a metal
  • C23C 28/04 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and only coatings of inorganic non-metallic material

28.

DEVICE FOR HOLDING ONE OR MORE ELECTRODES FOR ELECTRICAL DISCHARGE MACHINING, AND METHOD OF OBTAINING SAME

      
Document Number 03077103
Status In Force
Filing Date 2018-09-28
Open to Public Date 2019-04-04
Grant Date 2024-03-05
Owner SAFRAN (France)
Inventor
  • Ducas, Martin
  • Bechelany, Mirna

Abstract

The invention relates to creating an electrode holder for electrical discharge machining, comprising a body presenting a rectilinear part in which is fitted at least a first electrode passage duct. The body also presents a curved monobloc part in which is fitted (at least) a second curved dielectric fluid supply duct where a curved extension of said at least first duct goes through. The curved extension and the second curved duct are in ceramic with an arithmetic average roughness of: Ra < 2 .MU.m.

IPC Classes  ?

  • B23H 7/26 - Apparatus for moving or positioning electrode relatively to workpiece; Mounting of electrode
  • B23H 9/10 - Working turbine blades or nozzles
  • B23H 9/14 - Making holes
  • C04B 35/119 - Composites with zirconium oxide

29.

ALLOY TURBINE COMPONENT COMPRISING A MAX PHASE

      
Document Number 03076524
Status Pending
Filing Date 2018-09-21
Open to Public Date 2019-03-28
Owner
  • CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (CNRS) (France)
  • SAFRAN (France)
Inventor
  • Sallot, Pierre
  • Brunet, Veronique
  • Cormier, Jonathan
  • Drouelle, Elodie Marthe Bernadette
  • Dubois, Sylvain Pierre
  • Villechaise, Patrick

Abstract

The invention relates to a turbine component such as a turbine blade or a vane of a distributor, which comprises a polycrystalline substrate containing grains, wherein said substrate has at least one Ti3AlC2 phase and the mass fraction of said phase of the alloy is greater than 97%, characterised in that the average length of the grains is less than 50 µm, the average width-to-length ratio is between 0.4 and 0.6, and the average mesh volume of the Ti3AlC2 phase is less than 152.4 Å3.

IPC Classes  ?

  • B22F 3/105 - Sintering only by using electric current, laser radiation or plasma
  • B22F 5/00 - Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
  • B22F 5/04 - Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine blades
  • C04B 35/56 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides based on carbides
  • C22C 29/02 - Alloys based on carbides, oxides, borides, nitrides or silicides, e.g. cermets, or other metal compounds, e. g. oxynitrides, sulfides based on carbides or carbonitrides
  • C22C 29/06 - Alloys based on carbides, oxides, borides, nitrides or silicides, e.g. cermets, or other metal compounds, e. g. oxynitrides, sulfides based on carbides or carbonitrides based on carbides, but not containing other metal compounds

30.

TURBINE PART MADE OF SUPERALLOY COMPRISING RHENIUM AND/OR RUTHENIUM AND ASSOCIATED MANUFACTURING METHOD

      
Document Number 03076225
Status Pending
Filing Date 2018-09-21
Open to Public Date 2019-03-28
Owner SAFRAN (France)
Inventor
  • Saboundji, Amar
  • Jaquet, Virginie

Abstract

The invention relates to a turbine part, such as a turbine blade or a distributor fin, for example, comprising a substrate made of superalloy based on monocrystalline nickel, comprising rhenium and/or ruthenium, and having a ?'-NisAI phase that is predominant by volume and a ?-Ni phase, the part also comprising a sublayer made of metal superalloy based on nickel covering the substrate, characterized in that the sublayer has a ?'-NisAI phase that is predominant by volume and in that the sublayer has an average atomic fraction of aluminium of between 0.15 and 0.25, of chromium of between 0.03 and 0.08, of platinum of between 0.01 and 0.05, of hafnium of less than 0.01 and of silicon of less than 0.01. A process for manufacturing a turbine part comprising a step of vacuum deposition of a sublayer made of a superalloy based on nickel having predominantly by volume a ?'-NisAI phase, on a substrate made of superalloy based on nickel comprising rhenium and/or ruthenium, the sublayer having an average atomic fraction of aluminium of between 0.15 and 0.25, of chromium of between 0.03 and 0.08, of platinum of between 0.01 and 0.05, of hafnium of less than 0.01 and of silicon of less than 0.01.

IPC Classes  ?

  • F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion
  • C22C 19/00 - Alloys based on nickel or cobalt
  • C22C 19/05 - Alloys based on nickel or cobalt based on nickel with chromium
  • C23C 4/08 - Metallic material containing only metal elements
  • C23C 14/16 - Metallic material, boron or silicon on metallic substrates or on substrates of boron or silicon
  • C23C 28/00 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and

31.

CASTING SLURRY

      
Document Number 03076445
Status Pending
Filing Date 2018-09-21
Open to Public Date 2019-03-28
Owner SAFRAN (France)
Inventor Zhang, Wen

Abstract

The invention relates to a casting slurry for manufacturing shell moulds, comprising powder particles and a binder, and characterised in that it contains a surfactant. The invention also relates to the use of a casting slurry of this type for manufacturing a shell mould.

IPC Classes  ?

  • B22C 1/02 - Compositions of refractory mould or core materials; Grain structures thereof; Chemical or physical features in the formation or manufacture of moulds characterised by additives for special purposes, e.g. indicators, breakdown additives
  • B22C 1/18 - Compositions of refractory mould or core materials; Grain structures thereof; Chemical or physical features in the formation or manufacture of moulds characterised by the use of binding agents; Mixtures of binding agents of inorganic agents
  • B22C 1/20 - Compositions of refractory mould or core materials; Grain structures thereof; Chemical or physical features in the formation or manufacture of moulds characterised by the use of binding agents; Mixtures of binding agents of organic agents
  • B22C 9/04 - Use of lost patterns

32.

COATED TURBOMACHINE PART AND ASSOCIATED METHOD OF PRODUCTION

      
Document Number 03066848
Status Pending
Filing Date 2018-06-11
Open to Public Date 2018-12-20
Owner SAFRAN (France)
Inventor
  • Bianchi, Luc
  • Joulia, Aurelien
  • Bernard, Benjamin Dominique Roger Joseph

Abstract

A coated turbomachine part (20) comprises a substrate (21) and a layer for protection against the calcium and magnesium aluminosilicates CMAS (22) present on the substrate (21). The protective layer (22) comprises a first phase (220) of a material for protection against the calcium and magnesium aluminosilicates CMAS, capable of forming an apatite- or anorthite-type phase in the presence of calcium and magnesium aluminosilicates CMAS, and a second phase (221) comprising particles of at least one rare earth silicate REa dispersed in the first phase.

IPC Classes  ?

  • F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion
  • C23C 30/00 - Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process

33.

COATED TURBOMACHINE PART AND ASSOCIATED METHOD OF PRODUCTION

      
Document Number 03066302
Status Pending
Filing Date 2018-06-12
Open to Public Date 2018-12-20
Owner SAFRAN (France)
Inventor
  • Bianchi, Luc
  • Joulia, Aurelien
  • Bernard, Benjamin Dominique Roger Joseph

Abstract

A coated turbomachine part comprises a substrate (21) and a layer for protection against the calcium and magnesium aluminosilicates CMAS (24) present on the substrate (21). The layer (24) comprises a first phase (240) of a material for protection against the calcium and magnesium aluminosilicates CMAS and a second phase (241) comprising particles of a non-wetting material dispersed in the first phase.

IPC Classes  ?

  • F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion
  • C23C 4/04 - Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material

34.

PROCEDE DE FABRICATION AMELIORE D'UNE PIECE A MICROSTRUCTURE DUALE

      
Document Number 03064803
Status Pending
Filing Date 2018-06-01
Open to Public Date 2018-12-06
Owner SAFRAN (France)
Inventor Richard, Sebastien Jean

Abstract

A method for welding together at least two parts of green material, referred to as green parts, by means of co-sintering, comprising the following steps: - assembling the at least two green parts at a junction zone of said parts so as to form a green one-piece assembly, - de-binding the green one-piece assembly, and - sintering the one-piece assembly so as to obtain a dense one-piece assembly forming a final part, characterised in that the two green parts (10, 12) each have a composition of different powder, so as to produce a final part (1) having at least two parts with different grain sizes.

IPC Classes  ?

  • B22F 3/22 - Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor for producing castings from a slip
  • B22F 7/06 - Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting of composite workpieces or articles from parts, e.g. to form tipped tools

35.

HYBRID PROPULSION ARCHITECTURE FOR AN AIRCRAFT COMPRISING A MOTOR WITH TWO REVERSIBLE ELECTRIC MACHINES MOUNTED ON TWO SHAFTS

      
Document Number 03063699
Status Pending
Filing Date 2018-05-18
Open to Public Date 2018-11-22
Owner SAFRAN (France)
Inventor
  • Jaljal, Nawal
  • Desarnaud, Fabien

Abstract

The aircraft motor architecture comprises two reversible electric machines (3, 4), the rotors (10) of which are linked both to the low pressure shaft (1) and to the high pressure shaft (2) by transmissions (11, 12, 13, 14) alternately disengaged depending on the direction of rotation of the rotor (10), the transmissions comprising passive one-way clutches (15, 16, 17, 18), the engagement directions of which are opposed. Independent modes of operation of the machines, as a starter or as an electric generator of each of the shafts, are thus provided.

IPC Classes  ?

  • B64D 27/02 - Aircraft characterised by the type or position of power plant
  • B64C 11/48 - Units of two or more coaxial propellers
  • F02C 7/275 - Mechanical drives
  • F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user
  • B64D 27/33 - Hybrid electric aircraft

36.

BLADE COMPRISING AN IMPROVED COOLING CIRCUIT

      
Document Number 03059400
Status Pending
Filing Date 2018-04-10
Open to Public Date 2018-10-18
Owner SAFRAN (France)
Inventor
  • Flamme, Thomas Michel
  • Cariou, Romain Pierre
  • Paquin, Sylvain
  • Rollinger, Adrien Bernard Vincent

Abstract

The invention relates to a turbine blade comprising a blade root and a blade (13) extending radially outwards from the blade root (12), said blade (13) comprising a first inner cooling circuit comprising a lower surface cavity (33, 36) extending radially along the lower surface wall (16) and along a first inner wall (47, 45) arranged between the lower surface wall (16) and the upper surface wall (18), an upper surface cavity (34, 37) extending radially along the upper surface wall (18) and along a second inner wall (47, 43) arranged between the lower surface wall (16) and the upper surface wall (18). The first cooling circuit comprises an inner through-cavity (35, 38) defined between two through-walls (59, 57, 55, 53), each extending between the lower surface wall (16) and the upper surface wall (18). The lower surface cavity (33, 36), the upper surface cavity (34, 37) and the inner through-cavity (35, 38) are connected fluidically in series.

IPC Classes  ?

  • F01D 5/18 - Hollow blades; Heating, heat-insulating, or cooling means on blades

37.

METHOD FOR MANUFACTURING A COMPOSITE MATERIAL PART COMPRISING A BODY EXTENDED BY A REINFORCED ATTACHMENT END

      
Document Number 03059195
Status Pending
Filing Date 2018-04-09
Open to Public Date 2018-10-18
Owner SAFRAN (France)
Inventor
  • Lanfant, Nicolas Pierre
  • Coupe, Dominique Marie Christian
  • Faivre D'Arcier, Pierre

Abstract

The invention concerns a method for manufacturing a turbomachine flow straightener made from composite material having a blade extended by at least one attachment end (3, 4), comprising the operations of: forming a fibrous blank (13) from a three-dimensional fabric comprising warp threads (12) oriented in a direction (AR) corresponding to the longitudinal direction of the blade to be manufactured; dividing at least one end of the fibrous blank (13) by separating in order to constitute at least two sets of integrated layers (21, 22, 23); shifting at least one set of integrated layers (22, 23) in a planar configuration such that the warp threads (12) are inclined in this set of integrated layers (22, 23) relative to the orientation of the warp threads in the fibrous blank portion of the blade.

IPC Classes  ?

  • B29D 99/00 - Subject matter not provided for in other groups of this subclass
  • B29C 70/22 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure
  • B29C 70/24 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure
  • B29C 70/48 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM]
  • B29C 70/54 - Component parts, details or accessories; Auxiliary operations

38.

TURBINE BLADE HAVING AN IMPROVED STRUCTURE

      
Document Number 03059343
Status Pending
Filing Date 2018-04-10
Open to Public Date 2018-10-18
Owner SAFRAN (France)
Inventor
  • Paquin, Sylvain
  • Cariou, Romain Pierre
  • Flamme, Thomas Michel
  • Rollinger, Adrien Bernard Vincent

Abstract

The invention relates to an aviation turbine blade (10), characterised in that it comprises at least a first lower surface cavity (C2) and a first upper surface cavity (C3), each adjacent to a first through-cavity (C1) and a second through-cavity (C4), the first upper surface cavity (C3) being adjacent to the upper surface wall (24), the first lower wing surface cavity (C2) being adjacent to the lower surface wall (22), each of said first and second through-cavities (C1, C4) extending from the lower surface wall (22) as far as the upper surface wall (24), the second through-cavity (C4) comprising a first inner wall (P1) extending from the upper surface wall (24) as far as the first through-cavity (C1), and a second inner wall (P2) extending from the lower surface wall (22) as far as the first through-cavity (C1). The first (P1) and second (P2) inner walls are not connected.

IPC Classes  ?

  • F01D 5/18 - Hollow blades; Heating, heat-insulating, or cooling means on blades

39.

TURBINE COMPONENT MADE FROM SUPERALLOY AND ASSOCIATED MANUFACTURING METHOD

      
Document Number 03058619
Status Pending
Filing Date 2018-03-30
Open to Public Date 2018-10-04
Owner SAFRAN (France)
Inventor
  • Saboundji, Amar
  • Jaquet, Virginie

Abstract

The invention concerns a turbine component, such as a turbine blade or a distributor fin, for example, comprising a substrate made from single-crystal nickel superalloy, and a metal sublayer covering the substrate, characterised in that the metal sublayer comprises at least two elementary layers, including a first elementary layer and a second elementary layer, the first elementary layer being arranged between the substrate and the second elementary layer, each elementary layer comprising a ?'-Ni3Al phase, and optionally a ?-Ni phase, and in that the average atomic fraction of aluminium in the second elementary layer is strictly greater than the average atomic fraction of aluminium in the first elementary layer.

IPC Classes  ?

  • C23C 28/00 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and
  • C23C 14/02 - Pretreatment of the material to be coated
  • C23C 14/16 - Metallic material, boron or silicon on metallic substrates or on substrates of boron or silicon
  • F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion

40.

METHOD FOR PRODUCING A CONSOLIDATED FIBROUS PREFORM

      
Document Number 03055477
Status Pending
Filing Date 2018-03-05
Open to Public Date 2018-09-13
Owner
  • SAFRAN CERAMICS (France)
  • SAFRAN (France)
Inventor
  • Tesson, Thierry Guy Xavier
  • Carlin, Maxime Francois Roger
  • Thibaud, Simon
  • Dupont, Remy
  • Bohli, Ramzi

Abstract

A method for producing a consolidated fibrous preform intended for the manufacture of a part made of composite material, comprising the steps of: -shaping a fibrous texture (10) in a heated metal mould (20), the texture being pre-impregnated with a transient or transitory material (30), or shaping a fibrous texture in a metal mould and injecting a transient or transitory material into the fibrous texture held in shape in the metal mould, - cooling the mould, - removing the set fibrous preform from the mould, - coating the fibrous preform with a slip containing a powder of ceramic or carbon particles, - heat-treating the coated fibrous preform so as to form a porous shell around the fibrous preform by consolidation of the slip and so as to remove the transient or transitory material present in the fibrous preform, - consolidating the fibrous preform by gas-phase chemical infiltration.

IPC Classes  ?

  • C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
  • C04B 38/00 - Porous mortars, concrete, artificial stone or ceramic ware; Preparation thereof

41.

PROCESS FOR MANUFACTURING A POWER ELECTRONIC MODULE BY ADDITIVE MANUFACTURING, ASSOCIATED MODULE AND SUBSTRATE

      
Document Number 03049478
Status Pending
Filing Date 2018-01-05
Open to Public Date 2018-07-26
Owner SAFRAN (France)
Inventor
  • Khazaka, Rabih
  • Azzopardi, Stephane
  • Martineau, Donatien Henri Edouard

Abstract

A process for manufacturing a power electronic module (20) by additive manufacturing, the electronic module (20) comprising a substrate (21) including an electrically insulating sheet (24) having first and second opposite faces (24a, 24b), and a first metal layer (25a) that is placed directly on the first face (24a) of the insulating sheet (24) and a second metal layer (25b) that is placed directly on the second face (25b) of the insulating sheet (24). At least one of the metal layers (25a) is produced via a step (100) of depositing a thin copper layer and a step (110) of annealing the metal layer (25a, 25b), and the process furthermore comprises a step (120) of forming at least one thermomechanical transition layer (271 to 273, 274 to 276) on at least one of the first and second metal layers (25a, 25b), said at least one thermomechanical transition layer (271 to 273, 274 to 276) including a material having a thermal expansion coefficient lower than that of the metal of the metal layer (25a, 25b).

IPC Classes  ?

  • H01L 23/373 - Cooling facilitated by selection of materials for the device
  • H01L 21/48 - Manufacture or treatment of parts, e.g. containers, prior to assembly of the devices, using processes not provided for in a single one of the groups
  • H05K 1/02 - Printed circuits - Details
  • H05K 1/03 - Use of materials for the substrate
  • H01L 23/498 - Leads on insulating substrates

42.

CLUSTER MODEL AND SHELL FOR OBTAINING AN ACCESSORY FOR THE INDEPENDENT HANDLING OF FORMED PARTS, AND ASSOCIATED METHOD

      
Document Number 03048294
Status Pending
Filing Date 2017-12-22
Open to Public Date 2018-07-05
Owner
  • SAFRAN (France)
  • SAFRAN AIRCRAFT ENGINES (France)
Inventor
  • Niane, Ngadia Taha
  • Bohli, Ramzi
  • Galvin, Loic
  • Boukerma, Said

Abstract

The invention relates principally to a cluster model and a shell (1) for the production, by lost wax casting, of a plurality of turbomachine elements, the shell (1) comprising a central sprue (3) that is fluidically connected to a casting cup (2) for receiving the molten metal, and a plurality of shell elements (4). The shell (1) is characterized in that it further comprises a plurality of bottom feed conduits (5) for the shell elements (4) and a handling accessory shell (6) that is independent of the plurality of shell elements (4) and of their metal supply circuit, such that there is no fluidic connection to the shell elements (4), the handling accessory shell (6) being fluidically connected to the central sprue (3) so as to allow top-pour casting of the handling accessory shell (6).

IPC Classes  ?

43.

DEVICE AND METHOD FOR NON-DESTRUCTIVE CHARACTERISATION OF A MATERIAL

      
Document Number 03047200
Status Pending
Filing Date 2017-12-13
Open to Public Date 2018-06-28
Owner SAFRAN (France)
Inventor
  • Ducousso, Mathieu Loic
  • Jenson, Frederic

Abstract

A device (100) for non-destructive characterisation of a material (2), the device (100) comprising transmission/reception cells (10), each cell (10) being configured, in a transmission mode, for transmitting ultrasonic waves toward the material (2) to be characterised and, in a receiving mode, for receiving ultrasonic waves transmitted through said material (2), the non-destructive characterisation device (100) comprising a ring consisting of a plurality of adjacent angular sectors, each angular sector comprising a stack of transmission/reception cells (10) in a radial direction (DR) of the ring.

IPC Classes  ?

  • G01N 29/04 - Analysing solids
  • B06B 1/06 - Processes or apparatus for generating mechanical vibrations of infrasonic, sonic or ultrasonic frequency making use of electrical energy operating with piezoelectric effect or with electrostriction
  • G01N 29/22 - Investigating or analysing materials by the use of ultrasonic, sonic or infrasonic waves; Visualisation of the interior of objects by transmitting ultrasonic or sonic waves through the object - Details
  • G01N 29/24 - Probes
  • G01N 29/44 - Processing the detected response signal
  • G01S 15/89 - Sonar systems specially adapted for specific applications for mapping or imaging

44.

OPENLY POROUS ACOUSTIC FOAM, PROCESS FOR MANUFACTURE AND USES THEREOF

      
Document Number 03044699
Status Pending
Filing Date 2017-12-01
Open to Public Date 2018-06-07
Owner SAFRAN (France)
Inventor
  • Fotsing, Edith Roland
  • Dubourg, Arnaud
  • Ross, Annie

Abstract

There is provided a method of manufacturing an openly and highly porous thermoset foam, the method comprising the steps of mixing a thermosetting resin and crystals to form a mixture; applying pressure to the mixture to expel excess thermosetting resin, thereby producing a network of crystals touching each other with the thermosetting resin filling the interstices between the crystals of said network; curing the thermosetting resin in the mixture under pressure to produce a cured material; and contacting the cured material with a solvent for the crystals, thereby leaching the crystals out of the cured material, thereby obtaining said openly and highly porous thermoset foam. There is also provided a thermoset foam made of a thermoset and having a porosity of at least about 70%, wherein more than about 75% of the pores in the foam are connected to a neighboring pore.

IPC Classes  ?

  • C08J 9/26 - Working-up of macromolecular substances to porous or cellular articles or materials; After-treatment thereof by elimination of a solid phase from a macromolecular composition or article, e.g. leaching out

45.

METHOD FOR NON-DESTRUCTIVE TESTING OF A TURBOMACHINE PART

      
Document Number 03044925
Status Pending
Filing Date 2017-11-28
Open to Public Date 2018-05-31
Owner
  • SAFRAN (France)
  • SAFRAN AIRCRAFT ENGINES (France)
  • CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
  • "ASSOCIATION POUR LA RECHERCHE ET LE DEVELOPPEMENT DES METHODES ET PROCESSUS INDUSTRIELS" - A.R.M.I.N.E.S. (France)
Inventor
  • Remacha, Clement
  • Romero, Edward
  • Arnaud, Alexiane
  • Proudhon, Henry
  • Herbland, Thibault

Abstract

The invention relates to a method for testing the crystallographic orientation of at least one grain of a turbomachine part, comprising the steps of: a) emitting a beam of electromagnetic radiation through an elementary volume of the part and recording diffraction information on the electromagnetic radiation through the part; b) repeating step a) on a given area of the part, c) determining the crystalline spatial orientation of each of said elementary volumes and deducing therefrom the presence of at least one first crystallographic grain for which the elementary volumes are oriented according to the same crystallographic orientation; d) calculating the angular distance between the crystalline spatial orientation of said first grain and a predetermined direction taken from the part and comparing it to a first predetermined threshold value; e) determining a state of use of the part.

IPC Classes  ?

  • G01N 23/20 - Investigating or analysing materials by the use of wave or particle radiation, e.g. X-rays or neutrons, not covered by groups , or by using reflection of the radiation by the materials

46.

TURBOMACHINE PART COATED WITH A THERMAL BARRIER AND PROCESS FOR OBTAINING SAME

      
Document Number 03043107
Status Pending
Filing Date 2017-10-31
Open to Public Date 2018-05-17
Owner
  • SAFRAN (France)
  • SAFRAN AIRCRAFT ENGINES (France)
  • UNIVERSITE PAUL SABATIER TOULOUSE III (France)
  • CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
Inventor
  • Joulia, Aurelien
  • Malie, Andre Hubert Louis
  • Ansart, Florence
  • Delon, Elodie Marie
  • Duluard, Sandrine

Abstract

The invention relates to a turbomachine part (30) coated with at least one first thermal barrier layer (33) comprising a ceramic material and first ceramic fibers (34) dispersed in said first layer. The first layer may comprise a gradient of chemical composition between a thermal barrier material and a material for protection against calcium and magnesium aluminosilicates the content of which is greatest on an outer zone of the first layer, and/or the first layer may be porous and have a porosity gradient such that an outer portion of the first layer has a reduced porosity. The invention also targets a process for manufacturing such a part comprising the formation of the first layer on the part via a wet process.

IPC Classes  ?

  • C04B 41/87 - Ceramics
  • C04B 41/89 - Coating or impregnating for obtaining at least two superposed coatings having different compositions
  • F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion

47.

HEAT EXCHANGER

      
Document Number 03042754
Status Pending
Filing Date 2017-11-09
Open to Public Date 2018-05-17
Owner SAFRAN (France)
Inventor Toubiana, Ephraim

Abstract

Exchanger (1) of heat between a first fluid flowing in a longitudinal direction (X) and a second fluid, the said exchanger (1) comprising: two parallel plates (6) distant from one another; at least a first and second row (8a, 8b) of fins (9) arranged perpendicularly between the said plates (6), each fin (9) being delimited longitudinally by a first edge (10) and a second edge (11), the said first edge (10) comprising at each of its ends a region of connection with the corresponding plate (6); characterized in that the said connection regions of the said first edge (10) are respectively inclined with respect to a normal to the plates (6) in a plane (P) perpendicular to the said plates (6) and parallel to the direction (X), the said first edge (10) and the said second edge (11) of each of the fins (9) having identical profiles in the said plane (P).

IPC Classes  ?

  • F28F 3/04 - Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations the means being integral with the element
  • B33Y 30/00 - ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING - Details thereof or accessories therefor
  • B22F 3/105 - Sintering only by using electric current, laser radiation or plasma
  • B22F 5/00 - Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
  • F02C 7/08 - Heating air supply before combustion, e.g. by exhaust gases
  • F28D 9/00 - Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
  • F28D 21/00 - Heat-exchange apparatus not covered by any of the groups
  • F28F 3/06 - Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations the means being attachable to the element
  • F28F 21/08 - Constructions of heat-exchange apparatus characterised by the selection of particular materials of metal

48.

SUPERALLOY BASED ON NICKEL, MONOCRYSTALLINE BLADE AND TURBOMACHINE

      
Document Number 03041411
Status In Force
Filing Date 2017-10-24
Open to Public Date 2018-05-03
Grant Date 2024-04-16
Owner
  • SAFRAN (France)
  • SAFRAN AIRCRAFT ENGINES (France)
  • OFFICE NATIONAL D'ETUDES ET DE RECHERCHES AEROSPATIALES (France)
  • SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Rame, Jeremy
  • Belaygue, Philippe
  • Caron, Pierre
  • Delautre, Joel
  • Jaquet, Virginie
  • Lavigne, Odile

Abstract

The invention relates to a superalloy based on nickel, comprising, in mass percentages, 4.0 to 6.0 % of chromium, 0.4 to 0.8 % of molybdenum, 2.5 to 3.5 % of rhenium, 6.2 to 6.6 % of tungsten, 5.2 to 5.7 % of aluminium, 0.0 to 1.6 % of titanium, 6.0 to 9.9 % of tantalum, 0.0 to 0.7 % of hafnium, and 0.0 to 0.3 % of silicon, the rest consisting of nickel and potential impurities. The invention also relates to a monocrystalline blade (20A, 20B) comprising such an alloy and to a turbomachine (10) comprising such a blade (20A, 20B).

IPC Classes  ?

  • C22C 19/05 - Alloys based on nickel or cobalt based on nickel with chromium

49.

METHOD AND SYSTEM FOR MONITORING THE SOUNDNESS OF HELICOPTERS

      
Document Number 03041415
Status Pending
Filing Date 2017-10-18
Open to Public Date 2018-05-03
Owner
  • SAFRAN (France)
  • SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Razakarivony, Sebastien Philippe
  • Goudet, Francois

Abstract

The invention relates to a method for monitoring the soundness of helicopters comprising the determination of the severity of a plurality of flight missions of a plurality of helicopters, comprising a step for acquiring and storing flight data from helicopter flight missions, and a step for acquiring and storing maintenance data from the plurality of helicopters. The method is characterised in that said determination comprises a mission-type construction step, comprising a sub-step for constructing descriptors, a sub-step for partitioning the descriptors and a sub-step for allocating a mission type to each flight by associating the descriptor of said flight and a sub-set, in which this descriptor is found, and a step for interpreting the severity of the mission types, comprising a sub-step for estimating the severity models, and a sub-step for associating a severity model with each mission type determined in the mission type construction step.

IPC Classes  ?

  • B64F 5/00 - Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
  • B64C 27/04 - Helicopters
  • B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
  • G07C 5/00 - Registering or indicating the working of vehicles

50.

PART COMPRISING A NICKEL-BASED MONOCRYSTALLINE SUPERALLOY SUBSTRATE AND METHOD FOR MANUFACTURING SAME

      
Document Number 03040769
Status Pending
Filing Date 2017-10-19
Open to Public Date 2018-05-03
Owner SAFRAN (France)
Inventor
  • Saboundji, Amar
  • Jaquet, Virginie
  • Rame, Jeremy

Abstract

The invention relates to a method for manufacturing a part (1) comprising a nickel-based monocrystalline superalloy substrate (2). This method is characterised in that it comprises the steps that consist of: manufacturing a nickel-based monocrystalline superalloy substrate (2); forming a coating (3) on said substrate (2), comprising at least one layer (30) of a first type comprising aluminium and platinum, at least one layer (31) of a second type comprising aluminium, silicon, platinum and a layer (32) of a third type comprising nickel, aluminium, silicon and platinum, said layer (32) of the third type being the outermost layer of the stack of coating layers (3); and forming a layer (4) of silicon-doped alumina on said layer (32) of the third type.

IPC Classes  ?

  • C23C 28/00 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and
  • C23C 10/28 - Solid state diffusion of only metal elements or silicon into metallic material surfaces using solids, e.g. powders, pastes
  • C23C 14/16 - Metallic material, boron or silicon on metallic substrates or on substrates of boron or silicon
  • C23C 14/34 - Sputtering

51.

METHOD FOR NONDESTRUCTIVE INSPECTION BY ULTRASOUND OF A BONDED ASSEMBLY

      
Document Number 03041166
Status Pending
Filing Date 2017-10-24
Open to Public Date 2018-05-03
Owner SAFRAN (France)
Inventor
  • Ducousso, Mathieu Loic
  • Cuvillier, Nicolas

Abstract

The invention relates to a method for nondestructive inspection by ultrasound of a bonded assembly (1). The method comprises two steps, consisting of measuring a thickness of an adhesive joint (7) of the bonded assembly (1) by means of an ultrasound transducer (9) arranged on the bonded assembly (1) in a determined position, and measuring the degree of adhesion of parts of the bonded assembly (1) by means of the same ultrasound transducer (9) maintained in said determined position, the degree of adhesion being measured by means of ZGV Lamb waves (13).

IPC Classes  ?

  • G01N 29/04 - Analysing solids
  • G01N 29/26 - Arrangements for orientation or scanning
  • G01N 29/30 - Arrangements for calibrating or comparing, e.g. with standard objects
  • G01N 29/44 - Processing the detected response signal
  • G01N 29/46 - Processing the detected response signal by spectral analysis, e.g. Fourier analysis
  • G01N 29/52 - Processing the detected response signal using inversion methods other than spectral analysis, e.g. conjugated gradient inversion

52.

METHOD FOR COATING A SURFACE OF A SOLID SUBSTRATE WITH A LAYER COMPRISING A CERAMIC COMPOUND, AND COATED SUBSTRATE THUS OBTAINED

      
Document Number 03040347
Status Pending
Filing Date 2017-10-18
Open to Public Date 2018-04-26
Owner
  • COMMISSARIAT A L'ENERGIE ATOMIQUE ET AUX ENERGIES ALTERNATIVES (France)
  • SAFRAN (France)
Inventor
  • Bernard, Benjamin
  • Quet, Aurelie
  • Herve, Emmanuel
  • Bianchi, Luc
  • Joulia, Aurelien
  • Malie, Andre

Abstract

The invention relates to a method for coating at least one surface of a solid substrate with at least one layer comprising at least one ceramic compound by a suspension plasma spraying (SPS) technique, in which at least one suspension of solid particles of at least one ceramic compound is injected into a plasma jet, and then the thermal jet that contains the solid particle suspension is sprayed onto the surface of the substrate, by means of which the layer comprising at least one ceramic compound is formed on the surface of the substrate; method characterised in that, in the suspension, at least 90 vol% of the solid particles have a larger dimension (referred to as d90), such as a diameter, smaller than 15 µm, preferably smaller than 10 µm, and at least 50 vol% of the solid particles have a larger dimension, such as a diameter (referred to as d50), no smaller than 1 µm. The invention also relates to a substrate coated with at least one layer that can be obtained by said method. The invention also relates to a part comprising said coated substrate. The invention further relates to the use of said layer in order to protect a solid substrate against degradations caused by contaminants such as CMAS.

IPC Classes  ?

  • C23C 4/10 - Oxides, borides, carbides, nitrides or silicides; Mixtures thereof
  • C23C 4/11 - Oxides
  • C23C 4/134 - Plasma spraying
  • C23C 4/12 - Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
  • C23C 28/00 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and
  • C23C 28/04 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and only coatings of inorganic non-metallic material
  • F01D 5/02 - Blade-carrying members, e.g. rotors
  • F01D 5/06 - Blade-carrying members, e.g. rotors - Details thereof, e.g. shafts, shaft connections
  • F01D 5/12 - Blades

53.

TURBINE BLADE COMPRISING A COOLING CIRCUIT

      
Document Number 03038615
Status Pending
Filing Date 2017-09-28
Open to Public Date 2018-04-05
Owner SAFRAN (France)
Inventor
  • Rollinger, Adrien Bernard Vincent
  • Cariou, Romain Pierre
  • Flamme, Thomas Michel
  • Paquin, Sylvain

Abstract

Aeronautical turbine blade (10) comprising pressure-face-side cavities and suction-face-side cavities extending radially, and at least one central cavity situated in the central part of the blade (10) and surrounded by pressure-face-side and suction-face-side cavities, the blade (10) also comprising cooling circuits, in which at least a first cooling circuit (1) comprises: a first (A) and a second (B) cavity communicating with one another at an internal radial end (14) and at an external radial end (16) of the blade (10), a third cavity (C) communicating with the second cavity (B) at the external radial end (16), a fourth cavity (D) communicating with the third cavity (C) at the internal radial end (14), the first (A) and the second (B) cavities are fed jointly with cold air via a common air intake at the internal radial end (14), where the air flows in a first sense in the radial direction, the first cavity (A) being a pressure-face-side cavity, the second cavity (B) being a central cavity, the third cavity (C) and the fourth cavity (D) being suction-face-side cavities.

IPC Classes  ?

  • F01D 5/18 - Hollow blades; Heating, heat-insulating, or cooling means on blades

54.

METHOD FOR MANUFACTURING A PART OF ELECTROCONDUCTIVE MATERIAL BY ADDITIVE MANUFACTURING

      
Document Number 03035982
Status Pending
Filing Date 2017-09-07
Open to Public Date 2018-03-15
Owner SAFRAN (France)
Inventor Laurensan, Frederic

Abstract

Method for manufacturing at least one part (8) of electroconductive material by additive manufacturing on a bed of powder, characterised in that it comprises the steps of manufacturing the part on a support plate of a first additive manufacturing machine, layer by layer, said part being bounded by an external contour surface portion which is opposite and spaced apart from said support plate, and which is connected to said support plate by at least one bridge of support material of the part, providing a reference element (51) on the support plate in a predetermined position, mounting said support plate on a second machine (60) for cutting said at least one part, and using a wire (62-66) of said second machine for cutting by electrical discharge machining said at least one part by passing it between said at least one part and said support plate, along and at the level of said surface portion.

IPC Classes  ?

  • B22F 3/105 - Sintering only by using electric current, laser radiation or plasma
  • B29C 64/153 - Processes of additive manufacturing using only solid materials using layers of powder being selectively joined, e.g. by selective laser sintering or melting
  • B29C 67/00 - Shaping techniques not covered by groups , or

55.

METHOD FOR PRODUCING A THERMAL BARRIER SYSTEM ON A METAL SUBSTRATE OF A TURBO ENGINE PART

      
Document Number 03034760
Status Pending
Filing Date 2017-08-25
Open to Public Date 2018-03-01
Owner SAFRAN (France)
Inventor
  • Ben Salah, Nihad
  • Badreddine, Jawad
  • Joulia, Aurelien

Abstract

Method for producing a thermal barrier system on a metal substrate (1) of a turbo engine part, such as a high-pressure turbine blade, the thermal barrier system comprising at least one columnar ceramic layer (31,..., 3i,..., 3n), characterised in that the method comprises a step of compressing at least one of said at least one columnar ceramic layer (31,...3i,..., 3n).

IPC Classes  ?

  • C23C 28/00 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and
  • C23C 4/073 - Metallic material containing MCrAl or MCrAlY alloys, where M is nickel, cobalt or iron, with or without non-metal elements
  • C23C 4/134 - Plasma spraying
  • C23C 14/08 - Oxides
  • C23C 14/30 - Vacuum evaporation by wave energy or particle radiation by electron bombardment
  • C23C 14/58 - After-treatment

56.

METHOD FOR CREATING A NONPERMANENT MODEL

      
Document Number 03032098
Status In Force
Filing Date 2017-07-27
Open to Public Date 2018-02-01
Grant Date 2024-04-16
Owner
  • SAFRAN (France)
  • SAFRAN AIRCRAFT ENGINES (France)
Inventor
  • Rollinger, Adrien Bernard Vincent
  • Vollebregt, Mathieu Jean Luc
  • Tami Lizuzu, Joseph Toussaint
  • Herb, Vincent Marc
  • Guerche, Didier Maurice Marceau
  • Bohli, Ramzi

Abstract

The invention relates to a method of assembling a first core and a second core for the creation of a non-permanent model configured to form, by moulding using the lost-wax method, a component comprising a first cavity and a second cavity corresponding respectively to the first core and the second core. The invention is characterized in that the first and second cores are assembled using a first spacer piece, the first spacer piece being positioned between the first and second cores.

IPC Classes  ?

  • B22C 9/04 - Use of lost patterns
  • B22C 9/10 - Cores; Manufacture or installation of cores
  • B22C 21/14 - Accessories for reinforcing or securing moulding materials or cores, e.g. gaggers, chaplets, pins, bars

57.

PROCESS FOR MANUFACTURING A SHELL MOLD

      
Document Number 03031321
Status Pending
Filing Date 2017-07-21
Open to Public Date 2018-01-25
Owner
  • SAFRAN (France)
  • SAFRAN AIRCRAFT ENGINES (France)
Inventor
  • Zhang, Wen
  • Ragot, Patrice Henri Claude

Abstract

The invention relates to a process for manufacturing a shell mold having several layers, including at least one contact layer from a model of a part to be manufactured made of wax or other similar material, the process comprising a step of dipping the model in a contact slip forming the contact layer and comprising an inorganic or organic binder and a powder, wherein the powder is a mullite-zirconia composite.

IPC Classes  ?

  • B22C 1/08 - Compositions of refractory mould or core materials; Grain structures thereof; Chemical or physical features in the formation or manufacture of moulds characterised by additives for special purposes, e.g. indicators, breakdown additives for decreasing shrinkage of the mould, e.g. for investment casting
  • B22C 1/16 - Compositions of refractory mould or core materials; Grain structures thereof; Chemical or physical features in the formation or manufacture of moulds characterised by the use of binding agents; Mixtures of binding agents
  • B22C 9/04 - Use of lost patterns

58.

DIRECTIONAL SOLIDIFICATION COOLING FURNACE AND COOLING PROCESS USING SUCH A FURNACE

      
Document Number 03029438
Status In Force
Filing Date 2017-06-27
Open to Public Date 2018-01-04
Grant Date 2024-02-13
Owner
  • SAFRAN (France)
  • SAFRAN AIRCRAFT ENGINES (France)
Inventor
  • Niane, Ngadia Taha
  • Fargeas, Serge
  • Boukerma, Said
  • Tenne, Serge
  • Martin, Gilles

Abstract

Directional solidification cooling furnace (20) for a metal casting, comprising a cylindrical internal chamber (26) with a vertical central axis (X) and a mold support (28) positioned in the internal chamber (26), the internal chamber (26) comprising a casting zone (A) and a cooling zone (B), the casting zone (A) and the cooling zone (B) being superimposed on one another, the casting and cooling zones being thermally insulated from one another, when the mold support is positioned in the casting zone (A), by a fixed first heat shield (31) and a second heat shield (32) borne by the mold support (28), the casting zone (A) comprising at least a first heating device and the cooling zone (B) comprising a second heating device (60), the first and second heating devices being configured so that the temperature of the casting zone (A) is higher than the temperature of the cooling zone (B), the cooling zone (B) comprising an upper portion (B') and a lower portion (B") superposed on one another and thermally insulated from one another by a third heat shield (33), the upper portion (?') of the cooling zone (B) comprising the second heating device (60).

IPC Classes  ?

  • B22D 27/04 - Influencing the temperature of the metal, e.g. by heating or cooling the mould
  • C30B 11/00 - Single-crystal-growth by normal freezing or freezing under temperature gradient, e.g. Bridgman- Stockbarger method

59.

METHOD FOR THE PROTECTION OF A HAFNIUM-FREE, NICKEL-BASED MONOCRYSTALLINE SUPERALLOY PART AGAINST CORROSION AND OXIDATION

      
Document Number 03026710
Status Pending
Filing Date 2017-06-09
Open to Public Date 2017-12-14
Owner SAFRAN (France)
Inventor
  • Saboundji, Amar
  • Jaquet, Virginie

Abstract

The invention relates to a method for protecting a hafnium-free, nickel-based monocrystalline superalloy part (1) against corrosion and oxidation. Said method is characterized in that it involves at least the steps of: - manufacturing a hafnium-free, nickel-based monocrystalline superalloy part (1); - depositing a first hafnium-containing layer (2), an undercoat made of an alloy containing at least 10 atom % aluminum, and a second hafnium-containing layer on the part (1) such that a mixed layer (3) is formed, and depositing a third hafnium-containing layer (4) on the part (1); - performing a diffusion treatment in order for the first (2) and third (4) layers to diffuse such that a first interdiffusion region (21) is formed on the top portion of the part (1) and a second interdiffusion region (41) is formed on the surface of the mixed layer (3); - subjecting the second interdiffusion region (41) to an oxidation treatment so as to obtain a hafnium-doped alumina layer (42).

IPC Classes  ?

  • C23C 10/28 - Solid state diffusion of only metal elements or silicon into metallic material surfaces using solids, e.g. powders, pastes
  • C23C 12/00 - Solid state diffusion of at least one non-metal element other than silicon and at least one metal element or silicon into metallic material surfaces
  • C23C 28/00 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and

60.

PROCESS FOR MANUFACTURING A PART MADE OF NICKEL-BASED SUPERALLOY CONTAINING HAFNIUM

      
Document Number 03028263
Status Pending
Filing Date 2017-06-09
Open to Public Date 2017-12-14
Owner SAFRAN (France)
Inventor
  • Saboundji, Amar
  • Jaquet, Virginie

Abstract

The invention relates to a process for manufacturing a part made of nickel-based monocrystalline superalloy containing hafnium. This process is noteworthy in that it comprises the following successive steps consisting in: - manufacturing a nickel-based monocrystalline superalloy that is not doped with hafnium, - manufacturing a part from this superalloy, - directly depositing on said part a layer of hafnium having a thickness of between 50 nm and 800 nm, - carrying out a diffusion treatment of the hafnium so as to form an interdiffusion layer at the surface of said part and to thus obtain a part made of nickel-based monocrystalline superalloy containing hafnium.

IPC Classes  ?

  • C23C 10/28 - Solid state diffusion of only metal elements or silicon into metallic material surfaces using solids, e.g. powders, pastes

61.

MOULD FOR MANUFACTURING A SINGLE-CRYSTAL BLADE BY CASTING, INSTALLATION AND METHOD OF MANUFACTURE IMPLEMENTING SAME

      
Document Number 03025331
Status In Force
Filing Date 2017-06-01
Open to Public Date 2017-12-07
Grant Date 2023-10-03
Owner
  • SAFRAN (France)
  • SAFRAN AIRCRAFT ENGINES (France)
Inventor
  • Niane, Ngadia Taha
  • Boukerma, Said
  • Dillenseger, Serge
  • Gelebart, Julien
  • Grange, David
  • Hanny, Jean-Claude Marcel Auguste
  • Metron, Philippe

Abstract

The invention relates to a mould (3) made of a ceramic material intended to be used to mould a turbomachine blade from a molten metal, the blade comprising a base, a platform, a vane, and a root; the mould comprising: a cavity (4) having the shape of the blade, and an auxiliary grain duct (5) comprising a first portion (51) and a second portion (52) extending the first portion, said first portion leading, at one end (511), into a first part (40) of the cavity forming the base of the blade and, at another end (512), into a second part (412) of the cavity forming a spoiler of the blade platform, said second portion (52) leading, at one end (521), into said second part (412) of the cavity and, at another end, (522) into a third part (432) of the cavity forming a spoiler of the blade root. The invention also aims for an installation and a method of manufacture implementing such a mould.

IPC Classes  ?

62.

SUPPLY SYSTEM FOR SUPPLYING A MOULD WITH MOLTEN METAL, AND FACILITY AND MANUFACTURING METHOD IMPLEMENTING SAME

      
Document Number 03024373
Status Pending
Filing Date 2017-05-10
Open to Public Date 2017-11-16
Owner
  • SAFRAN (France)
  • SAFRAN AIRCRAFT ENGINES (France)
Inventor
  • Bohli, Ramzi
  • Niane, Ngadia Taha
  • Grange, David
  • Guerche, Didier Maurice Marceau
  • Boukerma, Said

Abstract

The invention concerns a supply system (5) for conveying a molten metal intended to mould a part, the system comprising a supply channel (51) made from ceramic material configured to allow the molten metal to flow by gravity inside said supply channel, said supply channel comprising a first portion (51a) extending in a first direction (A), and at least one second portion (51b) extending in a second direction (B) different to the first direction, said second portion being arranged downstream from the first portion and being linked to the first portion by a joint (52). The system further comprises a damping channel (54) comprising a first end (54a) opening in the joint and a second closed end (54b), said damping channel extending the first portion (51a) of the supply channel. The invention also concerns a facility comprising such a system, and a manufacturing method implementing same.

IPC Classes  ?

  • B22C 9/04 - Use of lost patterns
  • B22C 9/08 - Features with respect to supply of molten metal, e.g. ingates, circular gates, skim gates
  • B22D 27/04 - Influencing the temperature of the metal, e.g. by heating or cooling the mould

63.

METHOD FOR PRODUCING A PART FROM COMPOSITE MATERIAL BY INJECTING A LOADED SLIP INTO A FIBROUS TEXTURE

      
Document Number 03022103
Status Pending
Filing Date 2017-04-19
Open to Public Date 2017-11-02
Owner SAFRAN (France)
Inventor
  • Podgorski, Michael
  • Dambrine, Bruno
  • Ruiz, Edu

Abstract

A method for producing a part from composite material comprises positioning a fibrous texture (10) in a mould (110) comprising, in the lower portion of same, a part made from porous material (130) on which a first face (10b) of the texture (10) rests, injecting a liquid (150) containing a powder of refractory ceramic particles into the fibrous texture (10), under pressure, draining the liquid that has passed through the fibrous texture (10), by the part made from porous material (120), and retaining the powder of refractory ceramic particles inside said texture, by said part made from porous material (130). A rigid perforated member (140) is interposed between the bottom (111) of the mould (110) and the part made from porous material (130).

IPC Classes  ?

  • C04B 35/117 - Composites
  • B01D 29/05 - Filters with filtering elements stationary during filtration, e.g. pressure or suction filters, not covered by groups ;   Filtering elements therefor with flat filtering elements supported
  • B28B 7/34 - Moulds, cores, or mandrels of special material, e.g. destructible materials
  • B28B 7/36 - Linings or coatings
  • B28B 7/46 - Moulds; Cores; Mandrels characterised by means for modifying the properties of the moulding material for humidifying or dehumidifying
  • B29C 70/02 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising combinations of reinforcements and fillers incorporated in matrix material, forming one or more layers, with or without non-reinforced or non-filled layers
  • B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
  • C04B 35/14 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on oxides based on silica
  • C04B 35/18 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on oxides based on silicates other than clay rich in aluminium oxide
  • C04B 35/185 - Mullite
  • C04B 35/447 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on oxides based on phosphates
  • C04B 35/488 - Composites
  • C04B 35/56 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides based on carbides
  • C04B 35/565 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides based on carbides based on silicon carbide
  • C04B 35/58 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides based on borides, nitrides or silicides
  • C04B 35/584 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides based on borides, nitrides or silicides based on silicon nitride
  • C04B 35/626 - Preparing or treating the powders individually or as batches
  • C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
  • D03D 25/00 - Woven fabrics not otherwise provided for
  • F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion

64.

COOLED TURBINE VANE

      
Document Number 03016970
Status In Force
Filing Date 2017-03-09
Open to Public Date 2017-09-14
Grant Date 2024-04-23
Owner SAFRAN (France)
Inventor
  • Paquin, Sylvain
  • Rollinger, Adrien Bernard Vincent

Abstract

The invention relates to a turbomachine turbine vane comprising a root having a blade (12) comprising a leading edge (16) and a trailing edge (17) and a lower surface wall (14) and an upper surface wall (13), as well as: a manifold for cooling (18) the leading edge (16); a supply line (19) for collecting air from the root and supplying the manifold (18); a side cavity (23) extending along the upper surface wall (13) and supplied with air from the root, to form a heat shield facing the supply line (19); and a circuit forming a trombone comprising a middle portion (24) extending along the supply line (19) and extending laterally to the upper surface wall (13), said middle portion (24) being supplied by the supply line at the tip of the blade (12).

IPC Classes  ?

  • F01D 5/18 - Hollow blades; Heating, heat-insulating, or cooling means on blades

65.

CORE FOR CASTING A BLADE OF A TURBOMACHINE

      
Document Number 03015707
Status In Force
Filing Date 2017-02-27
Open to Public Date 2017-09-08
Grant Date 2023-07-04
Owner
  • SAFRAN AIRCRAFT ENGINES (France)
  • SAFRAN (France)
Inventor
  • Huchin, Patrick Emilien Paul Emile
  • Vollebregt, Matthieu Jean Luc
  • Rollinger, Adrien Bernard Vincent
  • Bechelany, Mirna

Abstract

The invention relates to a core (16) for casting a blade of a turbomachine, said core (16) comprising a first part (17) for defining a first cavity and a second part (18) of which at least one portion (19) defines a second cavity located between the first cavity and the tip of the blade, wherein: - said portion (19) of the second part (18) includes a through-hole that ends opposite the first part (17) so as to define, in the cast blade, an outer face of a duct for removing dust from the first cavity; - an alumina pin (27) which is secured to the end face (28) of the first part (17) extends into the through-hole to define the inner face of the duct; - centering means (29) are placed between the pin (27) and the through-hole so as to center the pin in relation to the through-hole, said centering means (29) being made of a material that is intended to dissolve before the blade is cast around the core (16).

IPC Classes  ?

  • B22C 9/10 - Cores; Manufacture or installation of cores
  • F01D 5/18 - Hollow blades; Heating, heat-insulating, or cooling means on blades
  • F01D 5/20 - Specially-shaped blade tips to seal space between tips and stator

66.

METHOD AND APPARATUS FOR MANUFACTURING A PART USING SUCCESSIVE DEPOSITIONS OF LAYERS

      
Document Number 03014855
Status Pending
Filing Date 2017-02-17
Open to Public Date 2017-08-24
Owner SAFRAN (France)
Inventor
  • Cornu, Daniel
  • Badreddine, Jawad
  • Dessoly, Vincent

Abstract

Method for manufacturing at least one portion of a part using successive deposition of layers, said method involving the steps of: a) depositing a first layer (110) of a molten metal on a substrate (80) such that a first metal strip is formed on the substrate; b) depositing a second layer of a molten metal on the first strip such that a second metal strip is formed on the first strip; and c) repeat steps a) and b) for each new metal layer to be deposited on a preceding strip until the at least one portion of the part has been formed; characterized in that after n deposition steps, where n is greater than or equal to 1, the method includes a compression step in which the obtained strip is compressed, and in that the compression takes place in the hot state, i.e. before the strip has entirely cooled down.

IPC Classes  ?

  • B22F 3/105 - Sintering only by using electric current, laser radiation or plasma
  • B23K 26/342 - Build-up welding
  • B22F 3/16 - Both compacting and sintering in successive or repeated steps
  • B29C 67/00 - Shaping techniques not covered by groups , or
  • C21D 7/06 - Modifying the physical properties of iron or steel by deformation by cold working of the surface by shot-peening or the like
  • C21D 9/50 - Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor for welded joints

67.

DEVELOPMENT OF A SOL-GEL ANTICORROSION TREATMENT

      
Document Number 03014296
Status In Force
Filing Date 2017-02-09
Open to Public Date 2017-08-17
Grant Date 2024-02-06
Owner
  • SAFRAN (France)
  • RBNANO (France)
  • SAFRAN LANDING SYSTEMS (France)
Inventor
  • Cambon, Jean-Baptiste
  • Esteban, Julien
  • Mafouana, Roland Rodrigue
  • Ruetsch, Jean-Philippe

Abstract

The invention relates to a process for treating a metal alloy part, characterized in that it comprises the following steps: - producing a stock formulation by mixing, in equal molar parts of silicon, an alcoholic solution of hydrolysed epoxysilane and an alcoholic solution of hydrolysed aminosilane, - mixing the stock formulation with a suspension comprising conductive nanowires in an amount by weight of between 0.1% and 10% relative to the total weight of the stock formulation in order to obtain a dilute formulation, and - depositing the dilute formulation on the part in order to obtain the coating.

IPC Classes  ?

  • C23C 18/12 - Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating by thermal decomposition characterised by the deposition of inorganic material other than metallic material
  • C09D 5/08 - Anti-corrosive paints

68.

METHOD FOR FORMING DUST-REMOVAL HOLES FOR A TURBINE BLADE AND ASSOCIATED CERAMIC CORE

      
Document Number 03014022
Status In Force
Filing Date 2017-02-10
Open to Public Date 2017-08-17
Grant Date 2023-12-05
Owner SAFRAN (France)
Inventor
  • Rollinger, Adrien Bernard Vincent
  • Bechelany, Mirna

Abstract

The invention relates to a ceramic core (10) used for the production of a hollow turbine blade for a turbomachine, using the lost-wax foundry technique, said blade comprising calibrated dust-removal holes extending from an apex of at least one cavity (22) and opening into a channel of the blade, each of said calibrated dust-removal holes being formed in a part of the core with a sufficient pre-determined height to ensure mechanical strength, said part of the core comprising a through-opening having an axis perpendicular to a longitudinal axis of the calibrated dust-removal hole and defining, on each side of the through-opening, a core cylinder having a pre-determined diameter corresponding to the dust-removal hole to be formed and a remaining core volume that is intended to be refilled after casting, such that the calibrated dust-removal hole is obtained without being pierced and without the use of connecting rods.

IPC Classes  ?

  • B22C 9/10 - Cores; Manufacture or installation of cores
  • F01D 5/18 - Hollow blades; Heating, heat-insulating, or cooling means on blades

69.

REFRACTORY CORE COMPRISING A MAIN BODY AND A SHELL

      
Document Number 03011498
Status In Force
Filing Date 2017-01-13
Open to Public Date 2017-07-20
Grant Date 2023-05-23
Owner SAFRAN (France)
Inventor
  • Grange, David
  • Niane, Ngadia Taha

Abstract

A refractory core (12) for manufacturing a hollow turbomachine blade (10) according to the lost-wax process comprises a main body (14) and at least one shell (16) connected to the main body (14) and defining a cavity (18) between the main body and the shell, the shell (16) being configured such that it contacts the blade (10) during manufacture.

IPC Classes  ?

  • B22C 9/10 - Cores; Manufacture or installation of cores

70.

AIRCRAFT ENGINE PART COMPRISING AN EROSION PROTECTIVE COATING AND PROCESS FOR MANUFACTURING SUCH A PART

      
Document Number 03005271
Status In Force
Filing Date 2016-11-16
Open to Public Date 2017-05-26
Grant Date 2023-10-10
Owner
  • SAFRAN HELICOPTER ENGINES (France)
  • SAFRAN (France)
Inventor
  • Gurt Santanach, Julien
  • Viola, Alain
  • Crabos, Fabrice

Abstract

The invention relates to an aircraft engine part (1) comprising at least one metal substrate (2) and an erosion protective coating (3) present on the substrate, the coating comprising at least one phase (4) comprising at least chromium in an atomic content greater than or equal to 45% and carbon in an atomic content between 5% and 20%, said phase comprising chromium carbides Cr7C3 and Cr23C6. The invention also relates to a process for manufacturing such a part in which a coating composition is deposited on the part by electrodeposition and the part is heat treated at a temperature between 250°C and 700°C.

IPC Classes  ?

  • C25D 5/50 - After-treatment of electroplated surfaces by heat-treatment
  • B32B 15/04 - Layered products essentially comprising metal comprising metal as the main or only constituent of a layer, next to another layer of a specific substance
  • B32B 15/16 - Layered products essentially comprising metal next to a particulate layer
  • B32B 33/00 - Layered products characterised by particular properties or particular surface features, e.g. particular surface coatings; Layered products designed for particular purposes not covered by another single class
  • C25D 3/06 - Electroplating; Baths therefor from solutions of chromium from solutions of trivalent chromium

71.

METHOD FOR MANUFACTURING A COMPONENT MADE OF COMPOSITE MATERIAL COMPRISING A BODY INTEGRAL WITH ONE OR MORE PLATFORMS

      
Document Number 03004161
Status In Force
Filing Date 2016-11-03
Open to Public Date 2017-05-11
Grant Date 2023-03-21
Owner SAFRAN (France)
Inventor
  • Lanfant, Nicolas Pierre
  • Pautard, Sebastien

Abstract

A method for manufacturing a component made of composite material having a body integral with at least one platform present at one end of the said body, the method comprising: - forming, from a fibrous blank, a preform of the component that is to be produced, by unfolding, on either side of a first part, segments (104a; 114a) of a second part and of a third part (106a; 116a) not connected to the first part, by shaping the segment (104a; 114a) unfolded from the second part and the segment (106a; 116a) unfolded from the third part to form preform parts of a platform of the component that is to be manufactured, and by folding the segment (102a; 112a) of the first part over on itself to fill a slot (108; 118) present at the separation between the second and third parts, - densifying the preform with a matrix in order to obtain a component made of composite material having at least one inbuilt platform.

IPC Classes  ?

  • B29D 99/00 - Subject matter not provided for in other groups of this subclass
  • B29C 70/22 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure
  • B29C 70/48 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM]
  • F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion

72.

DEVICE FOR GENERATING A STRUCTURAL-GRADIENT MICROSTRUCTURE ON AN AXISYMMETRIC PART

      
Document Number 03004391
Status In Force
Filing Date 2016-11-04
Open to Public Date 2017-05-11
Grant Date 2023-09-26
Owner SAFRAN (France)
Inventor
  • Franchet, Jean-Michel Patrick Maurice
  • Klein, Gilles Charles Casimir

Abstract

The invention relates to a device (1) for generating a structural-gradient microstructure on an axisymmetric mechanical part (P) hollowed out in the center thereof and initially having a fine-grained uniform structure. The device (1) includes a first heating means (2) that defines a first chamber for receiving the mechanical part (P) and is capable of heating the outer periphery (E) of said mechanical part (P) to a first temperature (T1) of greater than the solvus temperature. The device (1) includes a second heating means (3) that defines a second chamber arranged inside the first chamber and is capable of heating the inner periphery (I) of said mechanical part (P) to a second temperature (T2) of less than the solvus temperature. The space between the first chamber and the second chamber defines a recess (L) capable of accommodating the axisymmetric metal part (P) hollowed out in the center thereof.

IPC Classes  ?

  • C21D 1/00 - General methods or devices for heat treatment, e.g. annealing, hardening, quenching or tempering
  • C22F 1/10 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon

73.

METHOD AND MOULD FOR CREATING AN AERODYNAMIC ELEMENT COMPRISING RIBLETS

      
Document Number 03003818
Status Pending
Filing Date 2016-11-03
Open to Public Date 2017-05-11
Owner SAFRAN (France)
Inventor
  • Lanfant, Nicolas Pierre
  • Goncalves, Emilie

Abstract

The invention relates to a method for creating an aerodynamic element, notably for an aircraft, comprising an external face and plurality of parallel ribs and/or grooves formed on the said external face, the method consisting in creating the said element and its ribs and/or grooves simultaneously by use of a mould (22), characterized in that the method comprises: - a step of supplying a film (28) made of a deformable material, which has ribs and/or grooves that complement the ribs and/or the grooves of the said element, - a step of positioning the film (28) on a wall (26) of the mould (22), - a step of moulding the element, - a step of separating the element from the mould (22), simultaneously with the said film (28), and - a step of separating the film (28) from the element. The invention also relates to a mould (22) for implementing the method.

IPC Classes  ?

  • B29C 33/40 - Plastics, e.g. foam or rubber
  • B29C 33/38 - SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING - Details thereof or accessories therefor characterised by the material or the manufacturing process
  • B29C 33/42 - SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING - Details thereof or accessories therefor characterised by the shape of the moulding surface, e.g. ribs or grooves

74.

TURBINE ENGINE PART COVERED WITH A PROTECTIVE CERAMIC COATING, METHOD FOR MANUFACTURING AND FOR USING SUCH A PART

      
Document Number 02996217
Status In Force
Filing Date 2016-10-04
Open to Public Date 2017-04-13
Grant Date 2023-03-07
Owner SAFRAN (France)
Inventor
  • Podgorski, Michael
  • Berthod, Patrice
  • Mathieu, Stephane
  • Portebois, Leo
  • Vilasi, Michel

Abstract

The invention relates to a turbine engine part (10) comprising at least one substrate (11) and one ceramic coating (12) for protection against calcium and magnesium aluminum silicates present on the substrate, the ceramic coating including Al2O3 with a molar content of between 33% and 49%, Y3Al5O12 with a molar content of between 21% and 53%, and yttria-stabilized zirconia with a molar content of between 13% and 31%. The invention also relates to a method for manufacturing such a part and to a method for using such a part.

IPC Classes  ?

  • C23C 30/00 - Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process
  • F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion

75.

PROCESS FOR MANUFACTURING AN IMPREGNATED FIBROUS ASSEMBLY

      
Document Number 03001072
Status In Force
Filing Date 2016-10-05
Open to Public Date 2017-04-13
Grant Date 2023-03-07
Owner
  • SAFRAN AIRCRAFT ENGINES (France)
  • SAFRAN (France)
Inventor
  • Godon, Thierry Claude Henri
  • Podgorski, Michael

Abstract

The present invention relates in particular to a process for manufacturing an impregnated fibrous assembly, the process comprising at least the following steps: - introducing a first suspension (10) comprising a first powder of solid particles into an internal volume (2) delimited by an inner face (1a) of a first fibrous texture (1) of hollow shape placed in a mould, an outer face (1b) of the first fibrous texture (1) being present facing a wall (3) of the mould, - impregnating, by action of the centrifugal force, the first fibrous texture (1) with the first suspension (10) by rotating the mould about itself, - positioning, after impregnation of the first texture (1) with the first suspension, a second fibrous texture on the inner face (1a) of the first fibrous texture (1) in order to obtain a fibrous assembly, - introducing a second suspension comprising a second powder of solid particles into the internal volume (2) after positioning the second fibrous texture, and - impregnating, by action of the centrifugal force, the second fibrous texture with the second suspension by rotating the mould about itself in order to obtain the impregnated fibrous assembly.

IPC Classes  ?

  • C04B 35/622 - Forming processes; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
  • B22D 13/00 - Centrifugal casting; Casting by using centrifugal force
  • B22F 3/06 - Compacting only by centrifugal forces
  • B22F 3/11 - Making porous workpieces or articles
  • B22F 7/04 - Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting of composite layers with one or more layers not made from powder, e.g. made from solid metal
  • B28B 1/20 - Producing shaped articles from the material by centrifugal or rotational casting
  • B28B 1/28 - Producing shaped articles from the material by slip-casting, i.e. by casting a suspension or dispersion of the material in a liquid-absorbent or porous mould, the liquid being allowed to soak into or pass through the walls of the mould; Moulds therefor involving rotation of the mould
  • B28B 1/52 - Producing shaped articles from the material specially adapted for producing articles from mixtures containing fibres
  • B28B 21/30 - Centrifugal moulding
  • B29C 70/02 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising combinations of reinforcements and fillers incorporated in matrix material, forming one or more layers, with or without non-reinforced or non-filled layers
  • B29C 70/32 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core on a rotating mould, former or core
  • B32B 18/00 - Layered products essentially comprising ceramics, e.g. refractory products
  • C04B 35/111 - Fine ceramics
  • C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
  • C04B 41/45 - Coating or impregnating

76.

METHOD FOR IMPREGNATING A HOLLOW FIBROUS TEXTURE

      
Document Number 02983673
Status Pending
Filing Date 2016-05-23
Open to Public Date 2016-12-08
Owner
  • SAFRAN (France)
  • SAFRAN AIRCRAFT ENGINES (France)
Inventor
  • Godon, Thierry
  • Podgorski, Michael

Abstract

The invention relates in particular to a method for impregnating a hollow fibrous texture, the method comprising at least the following steps: injecting a first suspension (10) comprising a first powder of solid particles made of ceramic or carbon material into an inner space (2) defined by an inner surface (1a) of a hollow fibrous texture (1) placed in a mould, an outer surface (1b) of the fibrous texture (1) being presented opposite a wall (3) of the mould; and impregnating the fibrous texture (1) with the first suspension (10) by centrifugal force, by rotating the mould on itself, varying the speed of rotation of the mould during the impregnation of the texture (1) with the first suspension (10).

IPC Classes  ?

  • B28B 23/20 - Arrangements specially adapted for the production of shaped articles with elements wholly or partly embedded in the moulding material wherein the elements are reinforcing members the shaping being effected by centrifugal or rotational moulding
  • B29C 41/04 - Rotational or centrifugal casting, i.e. coating the inside of a mould by rotating the mould
  • C04B 35/84 - Impregnated or coated materials

77.

INTERMEDIATE CASING HUB FOR AN AIRCRAFT TURBOJET ENGINE INCLUDING A COMPOSITE OUTLET PIPE

      
Document Number 02985826
Status In Force
Filing Date 2016-05-13
Open to Public Date 2016-11-24
Grant Date 2023-04-11
Owner
  • SAFRAN AIRCRAFT ENGINES (France)
  • SAFRAN (France)
Inventor
  • Lacroix, Florian Benjamin Kevin
  • Mathias, Cyrille Francois Antoine
  • Texier, Idaline Francoise Chantal
  • Blaise, Maxime Marie Desiree

Abstract

The invention relates to an intermediate casing hub of an aircraft turbojet engine, which includes: an outer shroud (14) intended for defining a secondary flow space of a stream of secondary gas on the inside and an inter-flow area on the outside, the outer shroud (14) being provided with a secondary opening (29), and a bleed valve comprising an outlet pipe (30) made of composite material, located in the inter-flow area, wherein the outlet pipe (30) is attached to the outer shroud (14) at the secondary opening (29), at least one gasket (33) for sealing against air and fire being arranged between the outlet pipe (30) and the outer shroud (14), and the outlet pipe (30) made of composite material includes a draped composite wall (30a, 30b), made up of a plurality of folds impregnated with resin.

IPC Classes  ?

  • F02C 9/18 - Control of working fluid flow by bleeding, by-passing or acting on variable working fluid interconnections between turbines or compressors or their stages
  • F02K 3/075 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type controlling flow ratio between flows

78.

FIBROUS STRUCTURE FOR REINFORCING COMPONENTS MADE OF COMPOSITE MATERIAL WITH A GREAT VARIATION IN THICKNESS

      
Document Number 02976281
Status In Force
Filing Date 2016-02-09
Open to Public Date 2016-08-25
Grant Date 2022-11-01
Owner
  • SAFRAN CERAMICS (France)
  • SAFRAN (France)
Inventor
  • Lefebvre, Marie
  • Coupe, Dominique
  • Charleux, Francois

Abstract

A fibrous structure (200) comprises a plurality of weft layers (tl-t34) and of warp layers (C1-C12) connected to one another in a three-dimensional or multi-layer weave, the fibrous structure (200) comprising at least first and second parts (203, 204), which are adjacent in the warp direction, the first part (203) having, in a direction perpendicular to the warp and weft directions, a thickness that is greater than the thickness of the second part (204). Weft layers (tl3-t22) situated in the heart (2031) of the first part (203) of the fibrous structure (200) comprise braids (10). The weft layers (tl-tl2; t23-t34) extending on each side of the weft layers (tl3-t22) comprising the braids (10) and up to the skin (2032; 2033) of the first part (203) comprised threads or strands (20; 21; 22), the braids (10) having a cross section greater than the cross section of the threads or strands (20; 21; 22).

IPC Classes  ?

  • D03D 11/00 - Double or multi-ply fabrics not otherwise provided for
  • D03D 15/43 - Woven fabrics characterised by the material, structure or properties of the fibres, filaments, yarns, threads or other warp or weft elements used characterised by the structure of the yarns or threads with differing diameters
  • D03D 25/00 - Woven fabrics not otherwise provided for

79.

CONSTANT-VOLUME COMBUSTION MODULE FOR A TURBINE ENGINE, COMPRISING COMMUNICATION-BASED IGNITION

      
Document Number 02974296
Status In Force
Filing Date 2016-01-26
Open to Public Date 2016-08-04
Grant Date 2023-01-10
Owner SAFRAN (France)
Inventor Leyko, Matthieu

Abstract

The invention relates to a turbine engine combustion module (10), in particular for an aircraft turbine engine, designed to carry out constant-volume combustion, comprising: at least two combustion chambers (12A, 12B) arranged about an axis, each chamber (12A, 12B, 12C) comprising a compressed gas intake port (16) and a burnt gas exhaust port (18); and an ignition means that triggers combustion in the combustion chambers (12A, 12B, 12C). The module (10) comprises at least one duct (80) which establishes a communication between a first combustion chamber (12A) and at least one second combustion chamber (12B) in order to inject burnt gases from the first combustion chamber (12A) into the second combustion chamber (12B) so as to trigger combustion in the second combustion chamber (12B).

IPC Classes  ?

  • F23R 3/02 - Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
  • F02C 5/12 - Gas-turbine plants characterised by the working fluid being generated by intermittent combustion the combustion chambers having inlet or outlet valves, e.g. Holzwarth gas-turbine plants
  • F23R 3/48 - Flame tube interconnectors, e.g. cross-over tubes
  • F23R 7/00 - Intermittent or explosive combustion chambers

80.

CONSTANT-VOLUME COMBUSTION MODULE FOR A TURBINE ENGINE

      
Document Number 02974294
Status Pending
Filing Date 2016-01-25
Open to Public Date 2016-08-04
Owner SAFRAN (France)
Inventor Leyko, Matthieu

Abstract

The invention relates to a turbine engine combustion module (10), in particular for an aircraft turbine engine, designed to carry out constant-volume combustion, comprising: a plurality of combustion chambers (12) distributed angularly in a regular manner about an axis (A), each chamber (12) comprising a compressed gas intake port (16) and a burnt gas exhaust port (18), each intake (16)/exhaust (18) port being designed to be opened or closed by a corresponding common intake (28)/exhaust (30) rotary valve coaxial with the axis (A). The invention also relates to a turbine engine comprising a combustion module (10) of the type described.

IPC Classes  ?

  • F23R 3/02 - Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
  • F02C 5/12 - Gas-turbine plants characterised by the working fluid being generated by intermittent combustion the combustion chambers having inlet or outlet valves, e.g. Holzwarth gas-turbine plants
  • F23R 3/48 - Flame tube interconnectors, e.g. cross-over tubes
  • F23R 7/00 - Intermittent or explosive combustion chambers

81.

PHANTOM INTENDED FOR USE IN QUALITY CONTROL OF TOMOGRAPHIC IMAGES.

      
Document Number 02971654
Status In Force
Filing Date 2015-12-22
Open to Public Date 2016-06-30
Grant Date 2023-01-24
Owner
  • SAFRAN (France)
  • SAFRAN LANDING SYSTEMS (France)
  • SAFRAN AIRCRAFT ENGINES (France)
Inventor
  • Gay, Lionel Christian Jean-Loic
  • Arslan, Philippe
  • Rambourg, Yves
  • Chandelle, Andre

Abstract

The invention relates to a phantom (2) intended for use in quality control of tomographic images, comprising a cylindrical plate (4) produced from a homogeneous material having a density d1, two cylinders (6) inserted in the plate, the cylinders being produced from homogeneous materials having different densities d2 and d3, the density of one of the cylinders being greater than the density d1 of the plate and the density of the other cylinder being less than the density d1 of the plate, and a first series of pairs of holes (10i to 10n) of different diameters drilled in the plate, an axis of the holes of the first series being orientated axially with respect to an axis of rotation of the plate and the holes of a given pair being spaced apart by a distance equal to the diameter of said holes.

IPC Classes  ?

  • G01N 23/046 - Investigating or analysing materials by the use of wave or particle radiation, e.g. X-rays or neutrons, not covered by groups , or by transmitting the radiation through the material and forming images of the material using tomography, e.g. computed tomography [CT]

82.

METHOD FOR MANUFACTURING A REFRACTORY PART MADE OF COMPOSITE MATERIAL

      
Document Number 02972168
Status In Force
Filing Date 2015-12-18
Open to Public Date 2016-06-30
Grant Date 2022-07-12
Owner
  • SAFRAN (France)
  • SAFRAN AIRCRAFT ENGINES (France)
Inventor
  • Podgorski, Michael
  • Dambrine, Bruno Jacques Gerard
  • Molliex, Ludovic Edmond Camille
  • Billotte Cabre, Catherine
  • Ruiz, Edu
  • Turenne, Sylvain

Abstract

The invention relates to a method for manufacturing a part made of composite material, which includes the following steps: forming a fibrous texture (10) from refractory fibres; placing the fibrous texture (10) in a mould (110) including an impregnation chamber (101) comprising in the lower portion thereof a part made of porous material (120), wherein the impregnation chamber (101) is closed at the top thereof by a deformable impervious membrane (140) separating the impregnation chamber (101) from a compaction chamber (102); injecting a slurry (150) containing a powder of refractory particles into the impregnation chamber (101); injecting a compression fluid (160) into the compaction chamber (102) so as to force the slurry (150) to pass through the fibrous texture (10); draining the liquid from the slurry via the part made of porous material (120) and maintaining the powder of refractory particles inside said texture so as to obtain a fibrous preform (20) filled with refractory particles; drying the fibrous preform (20); removing the fibrous preform (20) from the mould; and sintering the refractory particles contained in the fibrous preform so as to form a refractory matrix in said preform.

IPC Classes  ?

  • C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
  • F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion

83.

METHOD FOR MANUFACTURING A FIBROUS PREFORM FILLED WITH REFRACTIVE CERAMIC PARTICLES

      
Document Number 02972170
Status In Force
Filing Date 2015-12-18
Open to Public Date 2016-06-30
Grant Date 2023-01-10
Owner
  • SAFRAN (France)
  • SAFRAN AIRCRAFT ENGINES (France)
Inventor
  • Droz, Nicolas
  • Liais, Ludovic
  • Podgorski, Michael
  • Billotte Cabre, Catherine
  • Ruiz, Edu
  • Turenne, Sylvain

Abstract

The invention relates to a method for manufacturing a fibrous preform filled with refractive ceramic particles (20), comprising the following steps: a) placing a fibrous structure comprising refractive ceramic particles into a mould cavity (2) defined by a mould (3) and a counter mould (4; 4'), b) injecting a slip, comprising a powder that has refractive ceramic particles (20) and is present in a liquid medium, into the porosity of the fibrous structure (1) in the mould cavity (2), the injection being carried out at least through a first surface (1a) or a first edge (1a') of said fibrous structure (1), and c) draining, through a component (5) made of porous material, the liquid medium from the slip that has penetrated the fibrous structure (1), the component made of porous material having a thickness of greater than or equal to 0.1 mm, the drainage being carried out at least through a second surface (1b) or a second edge of the fibrous structure (1) that is different from the first surface (1a) or the first edge (1a'), said component (5) made of porous material further allowing the powder having refractive particles (20) to be retained in the porosity of the fibrous structure (1) in order to obtain a fibrous preform filled with refractive particles (20), the component (5) made of porous material being between the mould (3) and the fibrous structure (1) or between the counter mould (4; 4') and the fibrous structure (1), and the component (5) made of porous material being between at least one outlet vent (16) and the fibrous structure (1), pumping being carried out in the region of the outlet vent (16) in order to drain the liquid medium through said outlet vent (16).

IPC Classes  ?

  • C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
  • B28B 1/52 - Producing shaped articles from the material specially adapted for producing articles from mixtures containing fibres
  • B28B 7/06 - Moulds with flexible parts
  • B28B 13/02 - Feeding the unshaped material to moulds or apparatus for producing shaped articles
  • B28B 23/00 - Arrangements specially adapted for the production of shaped articles with elements wholly or partly embedded in the moulding material
  • B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
  • C04B 35/622 - Forming processes; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
  • C04B 35/84 - Impregnated or coated materials
  • F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion

84.

METHOD FOR MANUFACTURING PART MADE OF COMPOSITE MATERIAL

      
Document Number 02972172
Status In Force
Filing Date 2015-12-18
Open to Public Date 2016-06-30
Grant Date 2022-07-12
Owner
  • SAFRAN (France)
  • SAFRAN AIRCRAFT ENGINES (France)
Inventor
  • Podgorski, Michael
  • Dambrine, Bruno Jacques Gerard
  • Molliex, Ludovic Edmond Camille
  • Billotte Cabre, Catherine
  • Ruiz, Edu
  • Turenne, Sylvain

Abstract

The invention relates to a method for manufacturing a part made of composite material, said method including the following steps: a step of forming a fibrous texture (10) from refractory fibres; a first impregnation step of impregnating the fibrous texture (10) with a first slurry (150) containing first refractory particles (151); a step of removing the liquid phase (152) from the first slurry (151) so as to allow only the first refractory particles (151) to remain inside said texture; a second impregnation step of impregnating the fibrous texture (20) with a second slurry (160) containing second refractory particles (161); a step of removing the liquid phase (162) from the second slurry (160) such as to allow only the second refractory particles (161) to remain inside said texture and to obtain a fibrous preform (30) filled with the first and second refractory particles (151, 161); and a step of sintering the first and second refractory particles (151, 161) in the fibrous preform (30) so as to form a refractory matrix inside said preform.

IPC Classes  ?

  • C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like

85.

DIFFUSER VANE MADE OF COMPOSITE MATERIAL FOR A GAS TURBINE ENGINE AND METHOD FOR MANUFACTURING SAME

      
Document Number 02957834
Status In Force
Filing Date 2015-08-20
Open to Public Date 2016-03-03
Grant Date 2023-03-28
Owner
  • SAFRAN AIRCRAFT ENGINES (France)
  • SAFRAN (France)
Inventor
  • Pautard, Sebastien
  • Briend, Maxime
  • Trousset, Emilie
  • Dunleavy, Patrick

Abstract

The invention relates to a diffuser vane (2) for a gas turbine engine, comprising a vane assembly (4) made of a composite material having a fibrous reinforcement densified by a matrix, the fibrous reinforcement being obtained from long fibres pre-impregnated and agglomerated in the form of a mat, the vane assembly being provided on at least one leading edge with a reinforcement strip (10-1), said reinforcement strip being made of a single strip of a unidirectional fabric or a textile, or of a stack of a plurality of pre-impregnated plies of a unidirectional fabric or a textile made of carbon fibres or glass fibres, and at least one platform (6, 8) positioned at a radial end of the vane assembly, the platform being made of a composite material having a fibrous reinforcement densified by a matrix, the fibrous reinforcement being obtained from pre-impregnated long fibres. The invention also relates to a method for manufacturing such a vane.

IPC Classes  ?

  • B29C 70/20 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in a single direction, e.g. roving or other parallel fibres
  • B29C 70/46 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
  • B29C 70/78 - Moulding material on one side only of the preformed part
  • F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion
  • F01D 9/02 - Nozzles; Nozzle boxes; Stator blades; Guide conduits

86.

PIVOT LINK ASSEMBLY

      
Document Number 02957358
Status In Force
Filing Date 2015-08-07
Open to Public Date 2016-02-18
Grant Date 2022-10-04
Owner
  • SAFRAN (France)
  • SAFRAN LANDING SYSTEMS (France)
Inventor
  • Renaud, Mathieu
  • Charrier, Jean-Sebastien
  • Greneche, Remi
  • Mounier, Anne
  • Pilato, Aurelie Eleonore

Abstract

The invention relates to a pivot link assembly (1) including a shaft (60) and first and second linking portions (12A, 40), each receiving the shaft (60) so as to enable the pivoting of said linking portions relative to one another. The first linking portion (12A) is axially arranged between a first end (62A) of the shaft (60) and a radial plane (PA1), whereas the second linking portion (40) is axially arranged between said radial plane (PAI) and the other end (62B) of the shaft (60). The shaft (60) is hollow and comprises an inner cross-section that has, in at least one first axial plane (Q) on a first section (T1) of the shaft (60) that is axially defined between a first end (62A) and the radial plane (PAI), a variable radial dimension (DA) that decreases as it axially approaches the radial plane (PAI). The assembly (1) includes a ring (20A, 20A') that is radially inserted between the shaft (60) and a bore of the first linking portion (12A) and has a variable radial thickness (E, E1, E2).

IPC Classes  ?

87.

METHOD FOR MANUFACTURING A PART MADE OF A COMPOSITE MATERIAL COMPRISING AT LEAST ONE PORTION FORMING A FORCE-INSERTION PORTION OR LOCAL THICKENED PORTION

      
Document Number 02941342
Status In Force
Filing Date 2015-07-02
Open to Public Date 2016-01-14
Grant Date 2022-07-19
Owner SAFRAN (France)
Inventor
  • Mandel, Robin
  • Dunleavy, Patrick
  • Trousset, Emilie

Abstract

Method for manufacturing a part made of a composite material, comprising precompaction of a first preform (220) of staple fibres having a length of between 8 mm and 100 mm. The first preform is positioned with a second preform (210) comprising a fibrous texture of staple fibres 15 impregnated with a second thermosetting resin and the polymerization of the first and second preforms. This makes it possible to make complex geometric parts out of composite materials that have no areas of weakness at the bonding interface between the subassemblies of the part.

IPC Classes  ?

  • B29C 70/84 - Moulding material on preformed parts to be joined
  • B29C 70/06 - Fibrous reinforcements only
  • B29C 70/42 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles

88.

METHOD AND DEVICE FOR DIGITAL RECONSTRUCTION OF AN ELEMENTARY VOLUME REPRESENTING A MICROSTRUCTURE OF COMPOSITE MATERIAL

      
Document Number 02950835
Status In Force
Filing Date 2015-06-01
Open to Public Date 2015-12-10
Grant Date 2023-08-15
Owner SAFRAN (France)
Inventor
  • Tranquart, Bastien
  • Mandel, Robin

Abstract

The invention relates to a method and device for digital reconstruction of an elementary volume representing a microstructure of composite material. The method includes: defining (F10) an elementary volume; filling the volume with digital elements modelling elements of fibres of the composite material, and extending longitudinally along a main axis, which includes: associating (F30) with each element a position in a plane of the space and an orientation of the main axis thereof; and consecutively positioning each element in the volume, in accordance with the position and the orientation which have been associated with same, said positioning including placing the element in contact (F40) with at least one wall of the elementary volume and/or at least one previously positioned element, and geometrically adapting (F50) the element to said at least one wall and/or to said at least one previously positioned digital element with which same is placed in contact, at least one portion of an element used to fill the volume undergoing, during the geometric adaptation, a deformation other than a tilting of the longitudinal axis thereof relative to the main axis of said element.

IPC Classes  ?

89.

METHOD AND DEVICE FOR ESTIMATION OF A QUALITY INDEX OF A 3-D IMAGE OF A PIECE OF COMPOSITE MATERIAL

      
Document Number 02950055
Status In Force
Filing Date 2015-05-22
Open to Public Date 2015-12-03
Grant Date 2022-10-18
Owner
  • SAFRAN AIRCRAFT ENGINES (France)
  • SAFRAN (France)
Inventor
  • Morard, Vincent
  • Parra, Estelle
  • Schneider, Julien
  • Tourais, David

Abstract

The method for estimation of a quality index of a 3-D image encoded in grey level of a piece of composite material, comprises: a step for obtaining (E20) a histogram (HIST) from the image, said histogram representing for each class of a plurality of classes each comprising at least one grey level, a number of voxels of the image having a grey level belonging to said class; an extraction step (E40) of a predetermined number of Gaussians present in the histogram; an estimation step (E60) for estimating at least one quality index of the image from parameters characterizing the Gaussians extracted from the histogram.

IPC Classes  ?

  • G01N 23/046 - Investigating or analysing materials by the use of wave or particle radiation, e.g. X-rays or neutrons, not covered by groups , or by transmitting the radiation through the material and forming images of the material using tomography, e.g. computed tomography [CT]

90.

FIRE PROTECTION OF A PART MADE OF A THREE-DIMENSIONAL WOVEN COMPOSITE MATERIAL

      
Document Number 02935977
Status In Force
Filing Date 2015-01-08
Open to Public Date 2015-07-16
Grant Date 2022-03-08
Owner
  • SAFRAN (France)
  • SNECMA (France)
Inventor
  • Mandel, Robin
  • Goncalves, Emilie
  • Le Borgne, Benedicte
  • Quillent, Helene
  • Rietsch, Jean-Christophe

Abstract

The invention relates to a method for fire protection (S) of a part (1) of a gas-turbine engine made of a composite material comprising a main fibrous reinforcement compregnated by a main matrix, the protection method (S) comprising the following steps: preforming (S1) a panel of prepreg (20) such as to grant same a shape corresponding to the shape of a surface (3) of the part (1) to be protected against fire, said panel of prepreg (20) comprising a secondary fibrous reinforcement compregnated by a secondary matrix; applying (S2) the panel of prepreg (20) thus preformed to the part (1); and securing (S3) the panel of prepreg (20) to the surface (3) by thermal treatment of the part (1) provided with said panel of prepreg (20) in order to obtain a fire-protection layer (2).

IPC Classes  ?

  • F01D 25/24 - Casings; Casing parts, e.g. diaphragms, casing fastenings
  • F02C 7/25 - Fire protection or prevention

91.

NON-INTRUSIVE MEASUREMENT OF THE VOLUME DENSITY OF A PHASE IN A PART

      
Document Number 02932942
Status In Force
Filing Date 2014-12-03
Open to Public Date 2015-06-18
Grant Date 2023-06-13
Owner SAFRAN (France)
Inventor
  • Morard, Vincent
  • Parra, Estelle
  • Tourais, David

Abstract

The invention concerns a method and a system for non-intrusively measuring the volume density of a specific phase in a part, comprising: - processing means (9) for producing a three-dimensional image (17) of said part (11), said image being formed by a three-dimensional grid of voxels of which the values indicate the arrangement of said specific phase in said part, - processing means (9) for associating a binary coefficient with each voxel of said three-dimensional image, thus constructing an initial three-dimensional matrix representation of binary coefficients, said binary coefficients being representative of a presence or absence of said specific phase in areas of said part corresponding to the voxels, - processing means (9) for convolving said initial matrix representation with a matrix convolution kernel corresponding to a predefined reference volume, said convolution being performed by implementing a composition of three (successive) one-dimensional convolutions in three separate directions, thus forming a resulting matrix representation of which each resulting coefficient represents a volume level (density) of said specific phase in said reference volume.

IPC Classes  ?

  • G01N 23/046 - Investigating or analysing materials by the use of wave or particle radiation, e.g. X-rays or neutrons, not covered by groups , or by transmitting the radiation through the material and forming images of the material using tomography, e.g. computed tomography [CT]

92.

METHOD FOR IMPREGNATION OF A FIBROUS PREFORM AND DEVICE FOR IMPLEMENTATION OF THE SAID METHOD

      
Document Number 02930813
Status In Force
Filing Date 2014-11-25
Open to Public Date 2015-06-11
Grant Date 2022-08-23
Owner
  • SNECMA (France)
  • SAFRAN (France)
Inventor
  • Henrio, Philippe
  • Godon, Thierry

Abstract

A method for impregnation of a fibrous preform (10) by an impregnation composition (20), the method comprising the following step: a) application of a liquid (30) onto a structure, the structure comprising: - a chamber (2) in which a fibrous preform (10) to be impregnated is present, the chamber (2) being defined between a rigid support (3) on which the fibrous preform (10) is placed and a wall (4), the wall (4) comprising a face (4a) located facing the fibrous preform (10), and - an impregnation composition (20), intended to impregnate the fibrous preform (10), the impregnation composition being present in the chamber (2), the liquid (30) being applied on the wall (4) of the opposite side of the chamber (2), the wall (4) being configured so that the face (4a) located facing the fibrous preform (10) retains its shape during application of the liquid (30), the applied liquid (30) enabling creation of a sufficient pressure to displace the wall (4) towards the rigid support (3) and impregnating the fibrous preform (10) with the impregnation composition (20).

IPC Classes  ?

  • B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
  • B29C 43/10 - Isostatic pressing, i.e. using non-rigid pressure-exerting members against rigid parts or dies
  • B30B 1/00 - Presses, using a press ram, characterised by the features of the drive therefor, pressure being transmitted directly, or through simple thrust or tension members only, to the press ram or platen

93.

A FIBER PREFORM FOR A HOLLOW TURBINE ENGINE VANE

      
Document Number 02926643
Status In Force
Filing Date 2014-10-03
Open to Public Date 2015-04-30
Grant Date 2021-11-09
Owner
  • SNECMA (France)
  • SAFRAN (France)
Inventor
  • Podgorski, Michael
  • Dambrine, Bruno Jacques Gerard
  • Le Hong, Son
  • Coupe, Dominique Marie Christian
  • Molliex, Ludovic Edmond Camille
  • Goering, Jonathan

Abstract

A fiber preform for a hollow turbine engine vane, the preform comprising a main fiber structure obtained by three-dimensional weaving and including at least one main part (41), wherein the main part (41) extends from a first link strip (44p), includes a first main longitudinal portion (46) suitable for forming essentially a pressure side wall of an airfoil, then includes an U-turn bend portion (45) suitable for forming essentially a leading edge or a trailing edge of the airfoil, then includes a second main longitudinal portion (47) facing the first main longitudinal portion (46) and suitable for forming essentially a suction side wall of the airfoil, and terminating at a second link strip (44q), wherein the first and second link strips (44p, 44q) are secured to each other and form a link portion (44) of the main fiber structure, and wherein the main longitudinal portions (46, 47) are spaced apart so as to form a gap between said main longitudinal portions (46, 47) suitable for forming a hollow in the airfoil.

IPC Classes  ?

  • B29C 70/48 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM]
  • B29B 11/16 - Making preforms characterised by structure or composition comprising fillers or reinforcements
  • B29C 70/24 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure
  • F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion

94.

FIBROUS STRUCTURE WITH GROUPING OF FLOATS

      
Document Number 02925836
Status In Force
Filing Date 2014-09-29
Open to Public Date 2015-04-09
Grant Date 2021-09-21
Owner
  • SNECMA (France)
  • SAFRAN (France)
Inventor
  • Gimat, Matthieu
  • Marchal, Yann
  • Coupe, Dominique

Abstract

A fibrous structure (200) comprises a preform portion (210) formed as a single piece by three-dimensional weaving between a first plurality of layers of threads and a second plurality of layers of threads, the preform portion corresponding to all or part of a fibrous reinforcement preform for a component made of composite. The fibrous structure (200) comprises, outside of the preform portion (210), one or more layers of two-dimensional woven fabric (220a, 220b), each layer of two-dimensional woven fabric grouping together the threads (2010a) of one same layer (201a) belonging at least to the first plurality of layers of threads and situated outside of the preform portion (210).

IPC Classes  ?

  • D03D 25/00 - Woven fabrics not otherwise provided for
  • B29C 70/22 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure
  • B29C 70/24 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure
  • F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion

95.

EQUIPMENT FOR ATTACHING A METAL REINFORCEMENT ONTO THE LEADING EDGE OF A TURBINE ENGINE BLADE, AND METHOD UTILIZING SUCH EQUIPMENT

      
Document Number 02911310
Status In Force
Filing Date 2014-04-28
Open to Public Date 2014-11-13
Grant Date 2021-12-21
Owner
  • SNECMA (France)
  • SAFRAN (France)
Inventor
  • Chauvin, Thierry
  • Varin, Franck Bernard Leon

Abstract

The invention relates to equipment for attaching a metal reinforcement (300) onto the leading edge (6) of a turbine engine blade (2), which includes a blade mounting (100) for receiving a blade while leaving surfaces of the leading edge of the blade exposed, and a mounting (200) for reinforcing the leading edge, onto which the blade mounting (100) is to be mounted, said mounting for reinforcing the leading edge including two side shims (208), between which the metal reinforcement (300) of the leading edge of the blade is positioned. The shims (208) can be moved closer and farther from one another and are each provided with a downdraft grate for grasping the metal reinforcement (300). The mounting (200) reinforcing the leading edge also includes heating elements for enabling polymerization of an adhesive film applied onto surfaces of the leading edge of the blade. The invention also relates to a method for attaching a metal reinforcement onto the leading edge (6) of a turbine engine blade (2) by means of such equipment.

IPC Classes  ?

  • B29C 65/48 - Joining of preformed parts; Apparatus therefor using adhesives
  • B29C 65/78 - Means for handling the parts to be joined, e.g. for making containers or hollow articles
  • F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion

96.

INJECTION MOULD FOR MANUFACTURING A ROTARY PART MADE OF A COMPOSITE MATERIAL HAVING EXTERNAL FLANGES, IN PARTICULAR OF A GAS TURBINE CASING

      
Document Number 02902849
Status In Force
Filing Date 2014-02-26
Open to Public Date 2014-09-04
Grant Date 2021-05-04
Owner SAFRAN (France)
Inventor Chauvin, Thierry

Abstract

The invention relates to an injection mould (4) for manufacturing a rotary part made of a composite material having external flanges, including a mandrel (2) on which a fibrous reinforcement (9) is intended to be supported and comprising a central wall, (6) the profile of which matches that of the part to be manufactured, two side plates (8), moulding wedges (12) for engaging with a non-covered surface of the fibrous reinforcement, and two external bells (14) for covering the moulding wedges and the side plates of the mandrel, sealing O-rings (24) being inserted between the bells and the side plates of the mandrel, the bells each being provided with an attachment flange (20) for engaging with one another, at least one sealing O-ring (26) being inserted therebetween, and the attachment flanges of the bells being clamped against one another.

IPC Classes  ?

  • B29C 70/48 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM]

97.

MONOBLOC PREFORM AND BLADE FOR TURBO MACHINE

      
Document Number 02891293
Status In Force
Filing Date 2013-11-12
Open to Public Date 2014-05-22
Grant Date 2021-01-12
Owner
  • SNECMA (France)
  • SAFRAN (France)
Inventor
  • Gimat, Matthieu
  • Coupe, Dominique Marie Christian

Abstract

Fibrous preform for a turbo machine blade, which preform is obtained by one-piece three-dimensional weaving. According to the invention, the preform comprises a first longitudinal portion (41) able to form a blade root, a second longitudinal portion (42) extending the first longitudinal portion and able to form a blade section, and a first transverse portion (51) extending transversely from the junction between the first and second longitudinal portions (41, 42) and able to form a first platform.

IPC Classes  ?

  • B29B 11/16 - Making preforms characterised by structure or composition comprising fillers or reinforcements
  • F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion

98.

METHOD FOR PRODUCING A PROPELLER BLADE FROM A COMPOSITE MATERIAL

      
Document Number 02862228
Status In Force
Filing Date 2013-01-24
Open to Public Date 2013-08-01
Grant Date 2019-06-25
Owner
  • SNECMA (France)
  • SAFRAN (France)
Inventor
  • Mathon, Richard
  • Foussard, Olivier
  • Marchal, Yann
  • Varin, Franck Bernard Leon

Abstract

The method for producing a propeller blade comprises the following steps -forming a spar (1) comprising a blade core (2); forming a blade preform (6) comprising a fibre fabric, said fabric having a separating area (7) where it is divided into two superposed skins (26, 27), the separating area comprising a location intended to receive the blade core; installing the blade preform in a tool (10) comprising an imprint (11) of said preform; opening the separating area (7) by moving the skins (26, 27) apart; installing the spar (1) by inserting the blade core (2) into the separating area (7); reclosing the separating area by moving the skins back together; injecting resin into the blade preform; polymerising the resin and machining the blade preform; a step for creating tracers (14), which are marks at predetermined positions on the blade preform (6), while forming said blade preform; a step for shaping the blade preform (6) in a predetermined position in the imprint after the step of installing the blade preform, matching the tracers (14) with target positions defined relative to the tooling, and a step of clamping the blade preform (6) in the imprint outside the separating area (7) before opening the separating area and until the spar (1) is installed.

IPC Classes  ?

  • B29B 11/16 - Making preforms characterised by structure or composition comprising fillers or reinforcements
  • B29D 99/00 - Subject matter not provided for in other groups of this subclass
  • B29C 31/08 - Feeding, e.g. into a mould cavity of preforms
  • B29C 33/00 - SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING - Details thereof or accessories therefor
  • B29C 70/08 - Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, with or without non-reinforced layers
  • B29C 70/48 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM]
  • B29C 70/54 - Component parts, details or accessories; Auxiliary operations
  • B29C 70/86 - Incorporating in coherent impregnated reinforcing layers
  • B64C 11/26 - Fabricated blades
  • B64C 27/00 - Rotorcraft; Rotors peculiar thereto