A motor device includes: an electric motor driven by AC drive electric power; an inverter that supplies the drive electric power to the electric motor; and a controller that generates a pulse signal for controlling the drive electric power using a first command signal indicating a target of the drive electric power and a carrier. The controller includes a carrier frequency setting unit that sets a carrier frequency of the carrier using a second command signal indicating the target of the drive electric power. The carrier frequency setting unit sets a carrier frequency in a section corresponding to a first phase range in one period of the second command signal to be lower than a carrier frequency in a section corresponding to a second phase range other than the first phase range.
H02P 21/06 - Commande basée sur le flux rotorique impliquant l’utilisation de détecteurs de position ou de vitesse du rotor
H02P 27/08 - Dispositions ou procédés pour la commande de moteurs à courant alternatif caractérisés par le type de tension d'alimentation utilisant une tension d’alimentation à fréquence variable, p.ex. tension d’alimentation d’onduleurs ou de convertisseurs utilisant des convertisseurs de courant continu en courant alternatif ou des onduleurs avec modulation de largeur d'impulsions
2.
METAL RECOVERY MATERIAL, AND METHOD FOR RECOVERING METAL FROM SOLUTION INCLUDING METAL ION OR METAL COMPLEX ION
C22B 3/18 - Extraction de composés métalliques par voie humide à partir de minerais ou de concentrés à l'aide de micro-organismes ou d'enzymes, p.ex. de bactéries ou d'algues
B01J 20/24 - Composés macromoléculaires d'origine naturelle, p.ex. acides humiques ou leurs dérivés
3.
METHOD FOR RECOVERING METAL FROM METAL ELEMENT-CONTAINING SUBSTANCE
A method for recovering a metal from a metal element-containing substance includes: bringing a metal element-containing substance into contact with a dissolving solution containing nitric acid and a salt to obtain a solution containing a metal ion or metal complex ion; and immersing an alga in the solution containing a metal ion or metal complex ion to produce a metal, wherein the concentration of nitric acid in the dissolving solution containing nitric acid and a salt is 2 to 50 mass%, and wherein the concentration of the salt in the dissolving solution containing nitric acid and a salt is 0.5 mass% or more.
C22B 3/18 - Extraction de composés métalliques par voie humide à partir de minerais ou de concentrés à l'aide de micro-organismes ou d'enzymes, p.ex. de bactéries ou d'algues
C22B 3/06 - Extraction de composés métalliques par voie humide à partir de minerais ou de concentrés par lixiviation dans des solutions inorganiques acides
4.
HYDROGEN PRODUCTION APPARATUS USING HYDROCARBON PYROLYSIS
The hydrogen production device 100 is equipped with: a first heating furnace 110 having a first housing tank in which a fluidized bed of a catalyst including one or more of iron, nickel, copper, and aluminum is formed and a heat transfer tube provided within the first housing tank, through which a heating medium passes; a second heating furnace 120 having a burner for burning a fuel to generate a combustion exhaust gas and a second housing tank in which a fluidized bed of the catalyst discharged from the first heating furnace is formed by the combustion exhaust gas; and a pyrolysis furnace 140 having a third housing tank in which a fluidized bed of the catalyst discharged from the second heating furnace is formed by a raw material gas including a hydrocarbon.
C01B 3/30 - Production d'hydrogène ou de mélanges gazeux contenant de l'hydrogène par décomposition de composés organiques gazeux ou liquides d'hydrocarbures avec des particules solides mobiles utilisant la technique du lit fluidisé
B01J 8/26 - Procédés chimiques ou physiques en général, conduits en présence de fluides et de particules solides; Appareillage pour de tels procédés les particules étant fluidisées selon la technique du "lit fluidisé" comportant au moins deux lits fluidisés, p.ex. installations de réaction et de régénération
5.
WORKPIECE CUTTING DEVICE AND WORKPIECE CUTTING METHOD
Provided is a workpiece cutting device capable of reliably cutting a workpiece in a short period of time without damaging portions other than seams and without leading to an increase in size of the device in a case where the device is used to cut a workpiece formed into a sheet shape by partially coupling a plurality of small pieces to each other, for example. A workpiece cutting device 1 that cuts a sheet-shaped or thin plate-shaped workpiece W into a first-side workpiece WR and a second-side workpiece WL includes a securing mechanism 3 that secures the first-side workpiece WR, a gripping and turning mechanism 4 that grips the second-side workpiece WL and turns the second-side workpiece WL about a seam Wa with the first-side workpiece WR as an axis, and a separating piece insertion mechanism 5 that separates the first-side workpiece WR and the second-side workpiece WL at a vulnerable portion formed at the seam Wa through a turning operation of the second-side workpiece WL performed by the gripping and turning mechanism 4.
A thrust foil bearing (3) includes: a base plate (30) including an insertion hole (30a) through which a shaft (1) is inserted, and a supporting surface (30b) expanding in a direction orthogonal to an axial direction of the insertion hole; a step member (50) placed on the supporting surface and formed of a different body from the base plate; and a back foil (20) extending in a circumferential direction of the insertion hole and in which one part of the back foil is supported by the supporting surface and another part of the back foil next to the one part in the circumferential direction is supported by the step member.
A floating-type base isolation system (100) includes: a liquid storage portion (110) storing liquid (114); a floating structure (120) floated and arranged on the liquid (114); and a gas accommodation space (132) formed at a position in contact with the liquid (114) and accommodating gas (134). A volume of the gas accommodation space (132) is set based on a natural frequency of a system that responds to a seismic wave propagating in fluid including the liquid (114) and the gas (134).
E04H 9/02 - Bâtiments, groupes de bâtiments ou abris conçus pour résister à des situations extérieures anormales, p.ex. à des bombardements, à des séismes ou à des climats extrêmes, ou pour se protéger de ces situations résistant aux séismes ou à l'effondrement du sol
F16F 15/023 - Suppression des vibrations dans les systèmes non rotatifs, p.ex. dans des systèmes alternatifs; Suppression des vibrations dans les systèmes rotatifs par l'utilisation d'organes ne se déplaçant pas avec le système rotatif utilisant des moyens fluides
A rotor (2) of an electrical rotating device (1) includes a rotor core (5), plural permanent magnets (6) mounted on an outer circumference of the rotor core (5), aretaining sleeve (7) that holds the permanent magnets (6) from their outer side, acooling fluid flow channel (P4) formed on each surface of the permanent magnets (6) ona side of the retaining sleeve (7) [or on each surface on a side of the rotor core 5], and a seal ring (8). The retaining sleeve (7) is configured of plural divided sleeves (7a) divided along a direction of a rotation axis (O) of the rotor (2). A seam is formed between adjacent divided sleeves (7a) in the plural divided sleeves (7a). The seal ring(8) covers the seam from an outer circumferential side [or an inner circumferential side].
H02K 1/22 - Parties tournantes du circuit magnétique
H02K 1/27 - Noyaux rotoriques à aimants permanents
H02K 9/19 - Dispositions de refroidissement ou de ventilation pour machines avec enveloppe fermée et circuit fermé de refroidissement utilisant un agent de refroidissement liquide, p.ex. de l'huile
9.
HYDROGEN PRODUCTION APPARATUS VIA HEATED CATALYST PARTICLES
A hydrogen production apparatus 100 includes a heating furnace 110 that burns fuel supplied by a fuel supply unit 190 and heats catalyst particles CAT, a cyclone 120 that is connected to a downstream side of the heating furnace 110 and separates the catalyst particles CAT and a combustion exhaust gas EX, and a thermal decomposition furnace 130 including a storage tank 132 that stores the catalyst particles CAT separated by the cyclone 120 and a raw material gas introduction unit 140 that introduces a raw material gas containing at least hydrocarbon from a lower portion of the storage tank 132.
C01B 3/30 - Production d'hydrogène ou de mélanges gazeux contenant de l'hydrogène par décomposition de composés organiques gazeux ou liquides d'hydrocarbures avec des particules solides mobiles utilisant la technique du lit fluidisé
H01M 8/0612 - Combinaison d’éléments à combustible avec des moyens de production de réactifs ou pour le traitement de résidus avec des moyens de production des réactifs gazeux à partir de matériaux contenant du carbone
C01B 32/05 - Préparation ou purification du carbone non couvertes par les groupes , , ,
C01B 3/56 - Séparation de l'hydrogène ou des gaz contenant de l'hydrogène à partir de mélanges gazeux, p.ex. purification par contact avec des solides; Régénération des solides usés
A jig (60) for inserting a packing (catalyst body (50),heat transfer enhancer (55)) into a flow passage (first flow passage (11), second flow passage (21)) of a reactor (1) extending in one direction or for removing the packing from the flow passage, includes: a pair of strip portions (61, 61) extending in parallel with each other, having a length longer than the flow passage; and link portions (62) arranged in an extending direction of the pair of strip portions (61, 61), linking the pair of strip portions (61, 61) and having lengths with which the pair of strip portions (61, 61) sandwich the packing therebetween.
An electric generator equipped in a multi-shaft gas turbine engine (10) for aircraft, includes: a rotor (31) attached to the rear end portion (17a) of a low-pressure shaft (17) rotatably supported by a bearing (29) in the gas turbine engine; a stator (32) provided around the rotor (31); wherein the electric generator has no structure to support the low-pressure shaft (17) and the rotor (31).
F02C 6/00 - Ensembles fonctionnels multiples de turbines à gaz; Combinaisons d'ensembles fonctionnels de turbines à gaz avec d'autres appareils; Adaptations d'ensembles fonctionnels de turbines à gaz à des applications particulières
F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
F02C 7/00 - Caractéristiques, parties constitutives, détails ou accessoires non couverts dans, ou d'un intérêt plus général que, les groupes ; Entrées d'air pour ensembles fonctionnels de propulsion par réaction
H02K 21/14 - Moteurs synchrones à aimants permanents; Génératrices synchrones à aimants permanents avec des induits fixes et des aimants tournants avec des aimants tournant à l'intérieur des induits
H02P 9/04 - Commande s'exerçant sur un moteur primaire non électrique et dépendant de la valeur d'une caractéristique électrique à la sortie de la génératrice
Disclosed is a radial foil bearing (3) provided with a bearing housing (12) having an insertion hole (12a), a top foil (9) arranged inside the insertion hole, and a foil structure (10, 11) interposed between the top foil and the bearing housing, wherein the foil structure has folded protrusions (10c) that are bent toward the outside of the insertion hole in the radial direction and bent back toward the inside of the insertion hole in the radial direction, and the folded protrusions engage mating grooves (15) formed in an end face of the foil bearing in the axial direction in which the insertion hole extends.
This strength evaluation method for evaluating the strength of a composite material in which a plurality of fiber layers are layered is provided with: a meandering-state measurement step (S4, S5) for measuring a meandering state of fibers in the plurality of fiber layers in the direction along the fiber layers; a meandering thickness measurement step (S6) for measuring a meandering thickness, which is the thickness in the layering direction of a portion in which meandering of fibers occurs in the plurality of fiber layers; and a strength evaluation step (S7, S8) for evaluating strength on the basis of the meandering state and the meandering thickness.
G01N 3/08 - Recherche des propriétés mécaniques des matériaux solides par application d'une contrainte mécanique par application d'efforts permanents de traction ou de compression
G01N 23/046 - Recherche ou analyse des matériaux par l'utilisation de rayonnement [ondes ou particules], p.ex. rayons X ou neutrons, non couvertes par les groupes , ou en transmettant la radiation à travers le matériau et formant des images des matériaux en utilisant la tomographie, p.ex. la tomographie informatisée
14.
THRUST FOIL BEARING, AND METHOD FOR MANUFACTURING BASE PLATE OF THRUST FOIL BEARING
A thrust foil bearing (3) is provided with a base plate (30) including a insertion hole (30a) through which a rotating shaft is inserted and supporting surfaces (31) disposed around the insertion hole (30a) on one side thereof in an axial direction, and back foils (20) disposed on the supporting surfaces (31), wherein: each supporting surface (31) comprises a plurality of inclined surfaces (31a to 31d) having an angle of inclination, inclined toward the other side of the base plate (30) in the axial direction, that becomes successively shallower with increasing distance toward the outside in the radial direction of the insertion hole (30a); each back foil (20) is divided by slits (24) into a plurality of divided regions (25) in the radial direction; and the plurality of divided regions (25) are supported by the plurality of inclined surfaces (31a to 31d).
This cooling system is provided with: a core casing (18) accommodating a compressor (12, 13), a combustion chamber (14), and a turbine (15, 16); a tail cone (28) forming, in conjunction with the core casing (18), at least a portion of an exhaust flow passage (23) of the turbine (15, 16); struts (27) linking the core casing (18) and a supporting body (26) of the tail cone (28); a housing (31) which is situated in the tail cone (28) to accommodate electrical equipment; and at least one main duct (40) providing communication between an internal space of the housing (31) and either an outlet flow passage (12a) of the compressor (12) or an exhaust port of a blower (34) situated in a gas turbine engine, through at least one of the struts (27) and through a radially outer side of the core casing (18).
A fuel supply control device (10) is configured to generate an operation amount used for feedback-controlling rotation of a gear pump (3) based on a deviation of a detected fuel flow rate with respect to a target flow rate, wherein the fuel supply control device generates the operation amount such that a rotation speed of the gear pump is equal to or greater than a predetermined lower limit rotation speed Nmin so as to protect a bearing of the gear pump.
A thrust foil bearing (3) according to the present invention comprises foil (10, 20) axially facing a thrust collar (4) attached to a shaft (1), and a case (8) supporting the foil and surrounding the thrust collar, wherein a cooling hole (50) is formed in the case.
F16C 17/06 - Paliers à contact lisse pour mouvement de rotation exclusivement pour charges axiales uniquement avec segments supportés obliquement, p.ex. paliers Michell
This thrust foil bearing (3) is equipped with a base plate (30) having an insertion hole (30a) through which a shaft (1) is inserted, and top foils (10) arranged at the periphery of the insertion hole. The top foils have: a slit (17) dividing the top foil into an inside region and an outside region in the radial direction of the insertion hole; a clamped portion (14) arranged in the outside region; an extension portion (13) extending from the clamped portion to the inside region; and slanted portions (12) that, in the inside region, are connected to the extension portion at an end edge on one side thereof in the circumferential direction of the insertion hole, extend from the extension portion toward the other side in the circumferential direction, and are slanted with respect to the level surface of the base plate expanding in a direction orthogonal to the axial direction of the insertion hole.
F16C 17/06 - Paliers à contact lisse pour mouvement de rotation exclusivement pour charges axiales uniquement avec segments supportés obliquement, p.ex. paliers Michell
A thrust foil bearing (3): comprising a base plate (30) having an insertion hole (30a) through which a shaft (1) is inserted and a back foil (20) arranged around the insertion hole (30a); and having a clamped section (14) extending from an end section of the back foil (20) in the circumferential direction of the insertion hole (30a) towards the outside in the radial direction of the insertion hole (30a).
F16C 17/06 - Paliers à contact lisse pour mouvement de rotation exclusivement pour charges axiales uniquement avec segments supportés obliquement, p.ex. paliers Michell
An artificial-satellite antenna installed in an artificial satellite (S) comprising a satellite body (1), said artificial-satellite antenna comprising solar cell panels (2A, 2B), radiators (3A, 3B), and conductors that are mechanically and electrically connected to the solar cell panels (2A, 2B), the solar cell panels (2A, 2B) and conductors being used as reflectors (Ra, Rb).
B64G 1/66 - Aménagements ou adaptations d'appareils ou d'instruments, non prévus ailleurs
B64G 1/44 - Aménagements ou adaptations des systèmes fournissant l'énergie utilisant des radiations, p.ex. panneaux solaires déployables
H01Q 1/28 - Adaptation pour l'utilisation dans ou sur les avions, les missiles, les satellites ou les ballons
H01Q 1/44 - ANTENNES, c. à d. ANTENNES RADIO - Détails de dispositifs associés aux antennes utilisant un équipement ayant une autre fonction principale servant en outre d'antenne
An aircraft air conditioning unit, addressing a need for increasing redundancy, includes: base units supplying compressed air to an air-conditioned space, each unit including compressors and turbines; and a temperature contoller for adjusting temperature of air from a compressor. Each base unit includes a switch, having first and second switching valves and a check valve, for changing a connection relationship between turbines. Each switching valve has input and output ports communicating with the air- conditioned space. The first valve has a further output port communicating with a first turbine and selectively outputs compressed air from a second turbine to either of its output ports. The check valve is opened/closed responsive to a pressure relationship between the further output port and the air-conditioned space. The second valve has another output port communicating with outside the aircraft and selectively outputs compressed air from the first turbine to either of its output ports.
B64D 13/08 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacement réservé au fret l'air étant climatisé l'air étant réchauffé ou refroidi
Conventionally, discharging ventilation air, which has been heated while passing through a heat exchanger, outside an aircraft fails to effectively use surplus energy. An inventive energy recovery device for an aircraft, directed to effectively utilizing surplus energy of the aircraft, includes: turbines provided between a cabin of the aircraft and an opening for discharging cabin air outside the aircraft and operated by only the cabin discharge air; power generators driven by the turbines; and cooling units for cooling an electrical instrument of the aircraft using the cabin discharge air. The turbines are operated by heated discharge air discharged from the cooling units. The turbines are provided in a one-to-one correspondence to the cooling units; and the power generators are provided in a one-to-one correspondence to the cooling units. A rotation shaft of each power generator is axially connected to each turbine.
This reaction device 1 comprises: a heat exchange part 2 having a first flow path 11 through which a reaction fluid is made to flow, and a second flow path 21 through which a heating medium is made to flow; an introduction path 5 for a temperature sensor, extending from an insertion port 5a provided on a side surface of the heat exchange part 2 to the first flow path or the second flow path; a piping 4 for the temperature sensor, connected to the side surface of the heat exchange part 2 and in communication with the introduction path 5 via the insertion port 5a; and a fixture 6 provided inside the piping 4. Provided in the fixture 6 is a guide hole 7 that extends toward a distal end 6a from a proximal end 6b and that opens toward the insertion port 5a of the introduction path 5. The guide hole 7 includes a taper hole 7b oriented from the proximal end 6b to the distal end 6a of the fixture 6.
B01J 19/24 - Réacteurs fixes sans élément interne mobile
G01K 1/143 - Supports; Dispositifs de fixation; Dispositions pour le montage de thermomètres en des endroits particuliers pour la mesure de la température de surfaces
The gas-liquid contact device comprises a gas-liquid contact unit, a liquid supply system, and a gas supply system. The gas-liquid contact unit includes a plurality of stages which are allocated so as to be arranged in the lateral direction. Each of the plurality of stages includes a plurality of vertical flat plates arranged parallel to each other at intervals. The liquid supply system supplies a liquid to the gas-liquid contact unit, and causes the liquid to be circulated along the array of the plurality of stages successively. The gas supply system supplies a gas to the gas-liquid contact unit, and causes the gas to be circulated along the array of the plurality of stages successively. The supplied liquid flows down on the plurality of vertical flat plates in each of the plurality of stages, and comes into contact with the supplied gas.
B01J 10/02 - Procédés chimiques généraux faisant réagir un liquide avec des milieux gazeux autrement qu'en présence de particules solides; Appareillage spécialement adapté à cet effet du type à couche mince
B01D 53/18 - Unités d'absorption; Distributeurs de liquides
F28F 25/02 - PARTIES CONSTITUTIVES OU AMÉNAGEMENTS, D'APPLICATION GÉNÉRALE, DES DISPOSITIFS ÉCHANGEURS DE CHALEUR OU DE TRANSFERT DE CHALEUR - Parties constitutives des réfrigérateurs à ruissellement pour répartir, faire circuler ou collecter le liquide
Provided is a fuel supply control device (F, F1) in which a parallel flow passageway of an orifice (8) and a pressurizing valve (7) is used as a complex pressurizing valve for a fuel supply amount, and which controls a fuel supply pump (3) on the basis of a before-after pressure difference of the complex pressurizing valve that has been detected by a pressure difference meter (9). When the rotational speed (N) of the fuel supply pump (3) is lower than a predetermined threshold value, the fuel supply pump (3) is controlled on the basis of a first fuel measurement quantity (Q1), and the fuel supply pump (3) is controlled on the basis of a second fuel measurement quantity (Q2).
This radial foil bearing (3) is provided with: a bearing housing (12) having an insertion hole (12a) into which a rotating shaft 1 is inserted; a base seat (30) disposed in the insertion hole (12a); a back foil (11) supported by the base seat (30) and having protrusions and recesses in the radial direction of the insertion hole (12a); and a top foil (9) supported by the back foil (11). The base seat (30) has a branch (P) separating in the radial direction of the insertion hole (12a) and is engaged with at least one of the bearing housing (12), the back foil (11), and the top foil (9).
A radial foil bearing (3) comprises a bearing housing (12) having an insertion hole (12a) through which a shaft is inserted, a back foil (11) disposed in the inner peripheral surface of the insertion hole (12a), a top foil (9) supported on the back foil (11), and a protrusion (40) that protrudes inward along the diameter of the insertion hole (12a) from the inner peripheral surface of the insertion hole (12a) and that is capable of supporting the top foil (9).
Provided is a method for removing an object to be removed from a structure (10) that has an object (11) to be removed made of a material having micropores into which a liquid can penetrate, and an object (12) to remain that is integrated with the object to be removed and that is made from a material not having micropores into which a liquid can penetrate, wherein a liquefied fluid (X) that vaporizes after injection is injected into the object to be removed.
This liquefied fluid supply system (3) supplies, to a nozzle (4), a liquefied fluid (X) which is to be evaporated after sprayed, the liquefied fluid supply system (3) being provided with: a supercooling unit (5) which converts the liquefied fluid to a supercooled liquid by cooling the liquefied fluid to a temperature lower than a saturation temperature; and a pressurizing unit (6) that pressurizes the liquefied fluid, which has been supercooled by the supercooling unit, and that supplies the pressurized fluid to the nozzle.
F17C 9/02 - Procédés ou appareils pour vider les gaz liquéfiés ou solidifiés contenus dans des récipients non sous pression avec changement d'état, p.ex. vaporisation
30.
PACKING, METHOD FOR MANUFACTURING SAME, AND LIQUID FILM-FORMING STRUCTURE
A filler has one or more filler elements, and the filler elements have a main body part having a flat liquid film-forming face and one or more wall parts vertically disposed with respect to the liquid film-forming face along a straight line. Side faces of the wall parts have inclined surfaces inclined at a prescribed angle with respect to the film-forming face, at the surface of the film formed by a liquid on the film-forming face.
B01J 19/32 - Eléments de remplissage en forme de grille ou d'éléments composés de plusieurs pièces pour constituer une unité ou un module dans l'appareil de transfert de chaleur ou de matière
B01D 53/18 - Unités d'absorption; Distributeurs de liquides
In a lining material peeling method of peeling a lining material (12), which is fixedly formed on a surface of a base material (11), from the base material, a liquefied fluid (X) which evaporates after injection is injected to a boundary between the base material and the lining material.
B29B 17/02 - Séparation de matières plastiques des autres matières
B05D 3/12 - Traitement préalable des surfaces sur lesquelles des liquides ou d'autres matériaux fluides doivent être appliqués; Traitement ultérieur des revêtements appliqués, p.ex. traitement intermédiaire d'un revêtement déjà appliqué, pour préparer les applications ultérieures de liquides ou d'autres matériaux fluides par des moyens mécaniques
32.
NOZZLE UNIT FOR INJECTING LIQUIFIED FLUID WHICH EVAPORATES AFTER INJECTION
This nozzle unit (6, 6A, 6B) injects a liquefied fluid that vaporizes after injection, wherein: the nozzle unit has a base portion (61), and a distal end portion (62) that has an injection opening (6d1) and is bent or curved with respect to and connected to the base portion; and the nozzle unit is equipped with a tubular portion (6b) in which there is formed a flow path (R) for guiding the liquefied fluid to a part including the distal end portion and the base portion.
B05B 15/00 - APPAREILLAGES DE PULVÉRISATION; APPAREILLAGES D'ATOMISATION; AJUTAGES OU BUSES - Parties constitutives des installations ou des appareillages de pulvérisation non prévus ailleurs; Accessoires
B05B 1/00 - Buses, têtes de pulvérisation ou autres dispositifs de sortie, avec ou sans dispositifs auxiliaires tels que valves, moyens de chauffage
A fuel supply device provided with: a first motorpump (10) that discharges fuel at a first flow rate toward an engine (X); a second motorpump (18) that discharges fuel at a second flow rate and merges this fuel with the fuel of the first flow rate; a first control device (C1, C11) that controls the first motorpump (10); and a second control device (C2, C22) that controls the second motorpump (18); the first control device (C1, C11) and the second control device (C2, C22) controlling the first motorpump (10) and the second motorpump (18) so that the total flow rate combining the first flow rate and the second flow rate reaches a fuel flow rate target value.
The energy management system (10) is an energy management system for a microgrid (1) including at least either one of an electrical load (30) and a renewable energy power-generation system (40), and an energy storage device (20), the energy management system including: a prediction unit (111) that predicts, at a fixed time interval, at least either one of an electricity demand and an amount of electricity generated front renewable energy, and an electricity fee, within a predetermined period; and an optimization unit (112) that performs optimization for an optimum charging/discharging plan for the energy storage device by using a prediction result from the prediction unit and in consideration of uncertainty in prediction.
H02J 3/00 - Circuits pour réseaux principaux ou de distribution, à courant alternatif
G06Q 50/06 - Fourniture d'électricité, de gaz ou d'eau
H02J 3/32 - Dispositions pour l'équilibrage de charge dans un réseau par emmagasinage d'énergie utilisant des batteries avec moyens de conversion
H02J 3/38 - Dispositions pour l’alimentation en parallèle d’un seul réseau, par plusieurs générateurs, convertisseurs ou transformateurs
H02J 7/35 - Fonctionnement en parallèle, dans des réseaux, de batteries avec d'autres sources à courant continu, p.ex. batterie tampon avec des cellules sensibles à la lumière
35.
HYDROPHILIZED MATERIAL, HYDROPHILIZED MEMBER, AND GAS-LIQUID CONTACT APPARATUS IN WHICH SAME IS USED
This hydrophilized material has a surface to which is imparted a surface roughness such that the arithmetic mean roughness is 0.3-1.0 µm and the average length of a roughness curve element is 0.1 mm or less. At least part of a hydrophilized member that contacts a liquid is configured from the hydrophylized material. The hydrophilized member, which is applied to a gas-liquid contact device having a gas-liquid contact part, a liquid supply system for supplying a liquid to the gas-liquid contact part, and a gas supply system for supplying a gas to the gas-liquid contact part, constitutes part of the gas-liquid contact part as a filler element, and continuously demonstrates wettability imparted due to the surface roughness thereof.
B01J 19/32 - Eléments de remplissage en forme de grille ou d'éléments composés de plusieurs pièces pour constituer une unité ou un module dans l'appareil de transfert de chaleur ou de matière
B01D 53/18 - Unités d'absorption; Distributeurs de liquides
B01D 53/78 - Procédés en phase liquide avec un contact gaz-liquide
A fluid disperser (10) is installed in a flow passage, and includes: a plate body (12) which has a first wall portion (12d) in a central region of a first top surface (12a) facing an upstream side, and a plurality of holes (12c) enabling a fluid to flow from the upstream side to the downstream side thereof; and a second wall portion (14) which is provided on the first top surface (12a) and includes an inner surface (14a) intersecting a straight line (LN) extending from the central region of the first top surface (12a) toward an outer edge portion thereof.
A sound-absorbing panel to be used affixed to a jet engine of an aircraft, provided with: a resin core layer 20 having a first surface, a second surface disposed on the side opposite from the first surface, and multiple partitions extending between the first surface and second surface so as to partition multiple cells; a resin first skin layer 30a laminated on the first surface of the core layer 20; and a resin second skin layer 40a laminated on the second surface of the core layer 20. The first skin layer 30a is disposed so as to face the external space while in use, and has multiple through-holes 60 for providing communication between internal spaces of the multiple cells S and external space faced by the first skin layer 30a. The core layer 20 has openings 50 for providing communication between the internal spaces of the multiple cells and external space of the core layer 20.
B64D 33/00 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs
B32B 3/12 - Produits stratifiés caractérisés essentiellement par le fait qu'une des couches comporte des discontinuités ou des rugosités externes ou internes, ou bien qu'une des couches est de forme générale non plane; Produits stratifiés caractérisés essentiellement par des particularismes de forme caractérisés par une couche discontinue, c. à d. soit continue et percée de trous, soit réellement constituée d'éléments individuels caractérisés par une couche d'alvéoles disposées régulièrement, soit formant corps unique dans un tout, soit structurées individuellement ou par assemblage de bandes indépendantes, p.ex. structures en nids d'abeilles
B32B 27/34 - Produits stratifiés composés essentiellement de résine synthétique comprenant des polyamides
B64C 1/00 - Fuselages; Caractéristiques structurales communes aux fuselages, voilures, surfaces stabilisatrices ou organes apparentés
F02C 7/045 - Entrées d'air pour ensembles fonctionnels de turbines à gaz ou de propulsion par réaction comportant des dispositifs destinés à supprimer le bruit
38.
AXIAL FLOW MACHINE AIRFOIL HAVING VARIABLE RADIUS ENDWALL FILLETS
A blade (12) of an axial flow machine is provided with: an airfoil part (13) having a dorsal surface (13a) and a ventral surface (13b); an end wall serving as a shroud (15) or a platform (14); and a fillet (16) provided along a connecting part between the airfoil part (13) and the end wall. The fillet (16) includes a first curved surface (16a) formed on at least a leading edge (13c) side and a trailing edge (13d) side of the airfoil part (13) on the dorsal surface (13a) side, and a second curved surface (16b) formed at a location other than the location at which the first curved surface (16a) is formed. The second curved surface (16b) has a smaller curvature radius than the first curved surface (16a).
Provided is a fan blade which is made of a composite material and which will not suffer damage even if a large foreign object collides with the fan blade. A fan blade (20) is provided with a blade body (21) composed of a composite material of thermoplastic resin or thermosetting resin and reinforcement fiber, a sheath (22) made of metal for at least partially covering a leading edge section (LE) of the blade body, and a guard (23) made of metal for at least partially covering a trailing edge section (TE) of the blade body. A trailing end section of the sheath and leading end section of the guard overlap in the thickness direction of the blade body on each plane of a positive pressure surface (SP) and a negative pressure surface (SS) of the blade body. In the overlapped sections (OL1, OL2), the leading end section of the guard is interposed between the trailing end section of the sheath and the blade body.
F01D 5/28 - Emploi de matériaux spécifiés; Mesures contre l'érosion ou la corrosion
F02C 7/00 - Caractéristiques, parties constitutives, détails ou accessoires non couverts dans, ou d'un intérêt plus général que, les groupes ; Entrées d'air pour ensembles fonctionnels de propulsion par réaction
Provided is a diffusion-bonded body welding method for bonding, by fusion welding, a diffusion-bonded body (10) formed by diffusion-bonding of metal members (12), and another member (16). The welding method comprises: a buffer layer forming step in which, in a welding region including a diffusion-bonded section (14) of the diffusion-bonded body (10), a buffer layer (20) having greater ductility than the diffusion-bonded section (14) is formed; and a welding step in which the welding region where the buffer layer (20) is formed and the other member (16) are bonded by fusion welding from above the buffer layer (20).
A reaction device (100), which serves as a heat treatment device, has: a heat transfer structure (43) disposed so as to be removable in a first flow path (31); first information acquisition units (70, 71) connected on an inlet side of the first flow path (31) and acquiring information for identifying the temperature and flow rate of a first fluid forming standard conditions for elapsed time; a second information acquisition unit (72) connected on the outlet side of the first flow path (31) and acquiring information for identifying the temperature of the first fluid for each unit of elapsed time; and a control unit (103) for finding the amount of heat exchange for elapsed time on the basis of the temperature and flow rate identified in the information acquired by the first information acquisition units (70, 71) and the second information acquisition unit (72) and predicting usage life of the heat transfer structure (43) on the basis of the amount of heat exchange.
B01J 19/24 - Réacteurs fixes sans élément interne mobile
F28D 7/16 - Appareils échangeurs de chaleur comportant des ensembles de canalisations tubulaires fixes pour les deux sources de potentiel calorifique, ces sources étant en contact chacune avec un côté de la paroi d'une canalisation les canalisations étant espacées parallèlement
A reactor (100) has: a first pipe (51) through which a third fluid (P) that includes a product generated by a reaction unit (101) flows; a second pipe (55) for supplying a second fluid (HC1) to a second flow path (31); a composition analyzing unit (71) provided so as to be connected to the first pipe (51); adjustment units (60, 63, 64) provided so as to be connected to the second pipe (55) and adjusting the flow rate (F) and the like of the second fluid (HC1); a control unit (103) for adjusting the flow rate (F) and the like of the second fluid (HC1) in the adjustment units (60, 63, 64) such that the temperature (Te2) of the third fluid (P) is a temperature such that the composition of the product maintains a reactivity (R) or yield prescribed in advance on the basis of the composition for the product analyzed by the composition analyzing unit (71); and a first temperature measurement unit (70) provided so as to be connected to the first pipe (51) and measuring the temperature (Te2) of the third fluid (P). The control unit (103) acquires information on the temperature (Te2) of the third fluid (P) from the first temperature measurement unit (70).
B01J 19/24 - Réacteurs fixes sans élément interne mobile
F28D 9/00 - Appareils échangeurs de chaleur comportant des ensembles de canalisations fixes en forme de plaques ou de laminés pour les deux sources de potentiel calorifique, ces sources étant en contact chacune avec un côté de la paroi d'une canalisation
F28F 3/08 - Eléments construits pour être empilés, p.ex. pouvant être séparés pour leur nettoyage
F28F 27/00 - Commandes ou dispositifs de sécurité spécialement adaptés pour les appareils d'échange ou de transfert de chaleur
43.
PRESSURE VESSEL WITH A BODY HAVING A RECTANGULAR CROSS-SECTION AND A CYLINDRICAL BODY FLANGE
[ABSTRACT] A pressure vessel includes a pressure vessel body provided with a flow channel through which a fluid is caused to flow, having a rectangular cross-sectional shape, and formed to extend in the fluid flow direction, a body flange provided at at least one end side of the pressure vessel body in a longitudinal direction and having a circular cross-sectional shape, and a connecting member. The connecting member has a first portion connected to the body flange, having a circular cross-sectional shape, and formed in a cylindrical shape, a second portion connected to the pressure vessel body, being larger in outer shape than the first portion, and formed in a cylindrical shape, and a connecting portion connecting the first portion and the second portion to each other and formed in a cylindrical shape with a shape changing to be gradually smaller from the second portion toward the first portion. Date Recue/Date Received 2020-08-13
F28F 9/12 - Dispositions pour obturer des éléments dans les boîtes de distribution ou plaques d'extrémité par joints démontables par raccordements du type à brides
F28D 7/16 - Appareils échangeurs de chaleur comportant des ensembles de canalisations tubulaires fixes pour les deux sources de potentiel calorifique, ces sources étant en contact chacune avec un côté de la paroi d'une canalisation les canalisations étant espacées parallèlement
This pressure container (10) is provided with a pressure container body (12) having a rectangular cross-sectional shape and formed extending in the direction in which fluid flows. The pressure container body (12) includes: a first flow passage which is formed in the longitudinal direction of the pressure container body (12) and through which a first fluid flows; a second flow passage which is formed in the longitudinal direction of the pressure container body (12) and through which a second fluid flows; a first fluid inlet/outlet opening (38) which is provided in one end surface of the pressure container body (12) in the longitudinal direction, is in communication with the first flow passage, and into which and from which the first fluid flows; and a second fluid inlet/outlet opening which is provided in the other end surface of the pressure container body (12) in the longitudinal direction, is in communication with the second flow passage, and into which and from which the second fluid flows. The pressure container body (12) has: an opening (50) provided in the one end surface of the pressure container body (12) in the longitudinal direction and in communication with the second flow passage; and a closure member (52) for closing the opening (50) in a mountable and removable manner.
F28F 3/08 - Eléments construits pour être empilés, p.ex. pouvant être séparés pour leur nettoyage
F28F 9/12 - Dispositions pour obturer des éléments dans les boîtes de distribution ou plaques d'extrémité par joints démontables par raccordements du type à brides
The present invention can easily stabilize a chlorosilane polymer without involving generation of a solid chlorosilane polymer. This method for stabilizing a chlorosilane polymer which is secondarily generated at a step of a chemical vapor deposition method using a chlorosilane-based gas, comprises: a step (S11) for diluting the chlorosilane polymer in an alcohol by bringing the chlorosilane polymer into contact with the alcohol to decompose the chlorosilane polymer into an alkoxide, hydrogen chloride, and hydrogen; and a step (S12) for hydrolyzing the alkoxide.
C23C 16/44 - Revêtement chimique par décomposition de composés gazeux, ne laissant pas de produits de réaction du matériau de la surface dans le revêtement, c. à d. procédés de dépôt chimique en phase vapeur (CVD) caractérisé par le procédé de revêtement
A reheating collection device for a gas phase process is provided with a container elongated in an axial direction along an axis to define a chamber, an inflow path and an exhaust path respectively in communication with the chamber and apart in the axial direction from each other, and a heater heating the chamber between the inflow path and the exhaust path.
C23C 16/44 - Revêtement chimique par décomposition de composés gazeux, ne laissant pas de produits de réaction du matériau de la surface dans le revêtement, c. à d. procédés de dépôt chimique en phase vapeur (CVD) caractérisé par le procédé de revêtement
H01L 21/205 - Dépôt de matériaux semi-conducteurs sur un substrat, p.ex. croissance épitaxiale en utilisant la réduction ou la décomposition d'un composé gazeux donnant un condensat solide, c. à d. un dépôt chimique
A liquid dispersing device (1) has: a tubular first wall portion (2) the center axis of which is an axis (L0) extending in a first direction; and a second wall portion (3) that is separated from the first wall portion (2) to the downstream side. The second wall portion (3) includes: at least one annular member (3a) or the like, and a disc-shaped member (3f) each having a flat surface with which a fluid having flowed through the internal space of the first wall portion (2) is caused to collide. The disc-shaped member (3f) is separated from the annular member (3a) or the like to the downstream side. The outer diameter of the annular member (3a) or the like is equal to or smaller than the inner diameter (d0) of the first wall portion (2). The outer diameter of the disc-shaped member (3f) is equal to or smaller than the outer diameter of an annular member (3e) that is the closest thereto.
B01J 19/24 - Réacteurs fixes sans élément interne mobile
F28F 9/02 - Boîtes de distribution; Plaques d'extrémité
F28F 9/22 - Dispositions pour diriger les sources de potentiel calorifique dans des compartiments successifs, p.ex. aménagement des plaques de guidage
F28F 13/12 - Dispositions pour modifier le transfert de chaleur, p.ex. accroissement, diminution en affectant le mode d'écoulement des sources de potentiel calorifique en créant une turbulence, p.ex. par brassage, par augmentation de la force de circulation
The filler has one or more thin-layer filler elements that are installed upright, the filler element having a main body portion with a planar liquid film formation surface, and one or more wall portions that are provided upright relative to the liquid film formation surface along a linear direction. The side surface of each wall portion has a curved portion at the base thereof connected to the liquid film formation surface, the curved portion curving so as to continue into the liquid film formation surface.
B01J 19/32 - Eléments de remplissage en forme de grille ou d'éléments composés de plusieurs pièces pour constituer une unité ou un module dans l'appareil de transfert de chaleur ou de matière
B01J 10/00 - Procédés chimiques généraux faisant réagir un liquide avec des milieux gazeux autrement qu'en présence de particules solides; Appareillage spécialement adapté à cet effet
49.
METHOD OF PRODUCING A SILICON COMPOUND MATERIAL AND APPARATUS FOR PRODUCING A SILICON COMPOUND MATERIAL
The silicon compound material production method according to the present invention comprises steps for: housing a preform of silicon carbide in a reaction furnace; impregnating the preform with silicon carbide by supplying a source gas containing methyltrichlorosilane into the reaction furnace; and reducing the generation of a gas-derived liquid or solid by-product by performing control so as to cause the temperature of the gas discharged from the reaction furnace to drop at a prescribed rate and by imparting a continuous thermal history to the gas.
C04B 35/565 - Produits céramiques mis en forme, caractérisés par leur composition; Compositions céramiques; Traitement de poudres de composés inorganiques préalablement à la fabrication de produits céramiques à base de non oxydes à base de carbures à base de carbure de silicium
A method for predicting the turbine outlet temperature of a gas turbine during future use on the basis of past usage records for the gas turbine, wherein parameters for environment/operation conditions scheduled for future use and a fan rotational frequency scheduled for future use are used as explanatory variables to predict the turbine outlet temperature during future use, as an objective variable, by means of a turbine outlet temperature model, and a coefficient for the explanatory variables is learned every time a learning trigger condition is fulfilled, thereby identifying the coefficient. During learning of the coefficient, the coefficient for the explanatory variables is identified on the basis of the result of regression learning of the explanatory variables and the objective variable of the turbine outlet temperature model performed using the aforementioned parameters, the fan rotational frequency, and the turbine outlet temperature during past use of the gas turbine.
F02C 7/00 - Caractéristiques, parties constitutives, détails ou accessoires non couverts dans, ou d'un intérêt plus général que, les groupes ; Entrées d'air pour ensembles fonctionnels de propulsion par réaction
F01D 25/00 - "MACHINES" OU MACHINES MOTRICES À DÉPLACEMENT NON POSITIF, p.ex. TURBINES À VAPEUR - Parties constitutives, détails ou accessoires non couverts dans les autres groupes ou d'un intérêt non traité dans ces groupes
F02C 9/00 - Commande des ensembles fonctionnels de turbines à gaz; Commande de l'alimentation en combustible dans les ensembles fonctionnels de propulsion par réaction alimentés en air ambiant
51.
CARBON DIOXIDE RECOVERY METHOD AND RECOVERY APPARATUS
A carbon dioxide collection device has: a separation device SP that, by utilizing carbon dioxide adsorption to and desorption from an adsorbent due to pressure fluctuations, separates carbon dioxide from a gas and discharges the remaining gas from which carbon dioxide has been removed; a drying device DR having a desiccant for drying a gas supplied to the adsorbent; and a regeneration system RG for supplying, to the drying device, the remaining gas discharged from the separation device as regeneration gas for regenerating the drying device adsorbent. The separation device has a pressurization device for pressurizing the supplied gas so that the adsorbent reaches a pressure at which carbon dioxide can be adsorbed. The collection device: has an energy conversion device EC for heating, by utilizing the pressure of post-regeneration gas discharged by the regeneration of the absorbent, the regeneration gas supplied to the drying device; compresses the regeneration gas by expansion of the post-regeneration gas; and heats by means of compression heat.
B01D 53/96 - Régénération, réactivation ou recyclage des réactifs
B01J 20/22 - Compositions absorbantes ou adsorbantes solides ou compositions facilitant la filtration; Absorbants ou adsorbants pour la chromatographie; Procédés pour leur préparation, régénération ou réactivation contenant une substance organique
52.
METHOD FOR INSPECTING ELECTROCONDUCTIVE COMPOSITE MATERIAL AND DEVICE FOR INSPECTING ELECTROCONDUCTIVE COMPOSITE MATERIAL
Provided is a method for inspecting an electroconductive composite material including disposing a detection magnetic field measurement unit, disposing a correction magnetic field measurement unit, applying a current, acquiring a detection magnetic field strength, acquiring a correction magnetic field strength, and detecting a portion in which arrangement of carbon fibers is disordered. The operation includes calculating a correction coefficient using the correction magnetic field strength and correcting the detection magnetic field strength using the correction coefficient.
G01N 27/72 - Recherche ou analyse des matériaux par l'emploi de moyens électriques, électrochimiques ou magnétiques en recherchant des variables magnétiques
53.
CARBON DIOXIDE RECOVERY METHOD AND RECOVERY DEVICE
Provided is a carbon-dioxide recovering device including: a separating device SP that separates carbon dioxide from a gas by utilizing adsorption and desorption of carbon dioxide due to pressure changes with respect to an adsorbent, and that discharges a residual gas from which carbon dioxide has been removed; a drying device DR that has a moisture adsorbent for drying the gas to be supplied to the separating device; a regenerating system RG that supplies the residual gas discharged from the separating device to the drying device so as to serve as a regenerating gas for regenerating the moisture adsorbent in the drying device; and a supplement system SU that supplies a supplement gas to the residual gas from the outside in accordance with the flow volume of the residual gas discharged from the separating device so that the flow volume of the regenerating gas reaches a predetermined volume. The regenerating gas, heated by means of heat exchange between the gas and the regenerating gas, is supplied to the drying device.
B01D 53/78 - Procédés en phase liquide avec un contact gaz-liquide
B01D 53/82 - Procédés en phase solide avec des réactifs à l'état stationnaire
B01D 53/96 - Régénération, réactivation ou recyclage des réactifs
B01J 20/22 - Compositions absorbantes ou adsorbantes solides ou compositions facilitant la filtration; Absorbants ou adsorbants pour la chromatographie; Procédés pour leur préparation, régénération ou réactivation contenant une substance organique
Tapered surface sections 21f, 22f are formed on inner-side surfaces of base sections 21a, 22a facing a flow path 14 at an outer band part 21 and an inner band part 22 of one of turbine stator blades 11, said turbine stator blades 11 being formed by a ceramic matrix composite material of two stator blade segments 10 which are disposed adjacent to each other with a space S therebetween. The tapered surface sections 21f, 22f are shaped into tapered surfaces which approach respective outer-side surfaces as the surfaces extend toward the tips of the base sections 21a, 22a, that is, toward end faces 21d, 22d. Thus, the thicknesses of the base sections 21a, 22a are smaller at the end faces 21d, 22d than at bent part sides connecting to a blade section 20 such that the depth of a dead space connecting to the flow path 14 is reduced.
This reactor uses heat exchange between a heat medium and a reaction fluid to promote the reaction of the reaction fluid. The reactor is provided with: a heat exchange body including a heat medium flow path through which the heat medium is made to flow, and a reaction flow path through which the reaction fluid is made to flow; at least one catalyst body which supports catalysts for accelerating the reaction of the reaction fluid, and which is detachably installed inside the reaction flow path; and holding members which are capable of being inserted into and removed from the reaction flow path while the catalyst body is in a held state. The holding members include: extension parts which extend so as to match the shape of the reaction flow path in the extension direction, and which are capable of engaging with the catalyst body; and restriction parts which are provided to the extension parts, and which are capable of restricting movement of the catalyst body in the extension direction of the extension parts.
C07C 1/04 - Préparation d'hydrocarbures à partir d'un ou plusieurs composés, aucun d'eux n'étant un hydrocarbure à partir d'oxydes de carbone à partir de monoxyde de carbone avec de l'hydrogène
C07C 9/02 - Hydrocarbures saturés acycliques de un à quatre atomes de carbone
F28D 9/00 - Appareils échangeurs de chaleur comportant des ensembles de canalisations fixes en forme de plaques ou de laminés pour les deux sources de potentiel calorifique, ces sources étant en contact chacune avec un côté de la paroi d'une canalisation
F28F 3/06 - Eléments ou leurs ensembles avec moyens pour augmenter la surface de transfert de chaleur, p.ex. avec des ailettes, avec des évidements, avec des ondulations les moyens pouvant être fixés sur l'élément
F28F 3/08 - Eléments construits pour être empilés, p.ex. pouvant être séparés pour leur nettoyage
56.
MATERIAL SHAPE SIMULATION APPARATUS, MATERIAL SHAPE SIMULATION METHOD, AND THREE-DIMENSIONAL WOVEN FIBER COMPONENT MANUFACTURING METHOD
[Problem] To provide a material shape simulation device that more accurately simulates deformation of a three-dimensional woven fiber material. [Solution] A material shape simulation device 100 equipped with: an orientation vector field generation unit 210 that generates a model shape orientation vector field with respect to a three-dimensional mesh with a model shape of a three-dimensional woven material wherein a plurality of two-dimensional woven fabrics comprising X-threads extending in the X-direction and Y-threads extending in the Y-direction are stacked on one another by means of Z-threads extending in the Z-direction; a parameterization unit 220 that searches for gradient vectors for calculating, from the model shape orientation vector field, a material shape orientation vector field, which is an orientation vector field for the material shape prior to deformation of the model shape; and an orientation vector updating unit 230 that updates the model shape orientation vector field by applying, between the model shape orientation vector field and the material shape orientation vector field, a condition under which the volume is preserved and a condition under which the X-threads and the Y-threads respectively do not expand or contract.
G06F 30/20 - Optimisation, vérification ou simulation de l’objet conçu
D03C 19/00 - Méthodes ou dispositifs relatifs à la mise en carte ou à la création de dessins, non prévus dans les autres groupes de la présente sous-classe
G05B 19/4099 - Usinage de surface ou de courbe, fabrication d'objets en trois dimensions 3D, p.ex. fabrication assistée par ordinateur
Disclosed is a method of manufacturing an airfoil structure used in a jet engine. The airfoil structure includes airfoils, a support supporting the airfoils at their lower ends, and a case covering upper ends of the airfoils. Each airfoil includes an airfoil body, and an airflow generator, provided to the airfoil body, producing induced airflow by plasma. A process of forming the airflow generator includes a first electrode forming step of forming a first electrode on the airfoil body, a dielectric layer forming step of forming a dielectric layer by forming ceramic powder into a film to cover the first electrode through room temperature impact consolidation, and a second electrode forming step in which a second electrode is formed so that the second electrode is exposed at the surface of the dielectric layer, is electrically connected to the first electrode, and is applied with an alternating current voltage.
F02C 7/00 - Caractéristiques, parties constitutives, détails ou accessoires non couverts dans, ou d'un intérêt plus général que, les groupes ; Entrées d'air pour ensembles fonctionnels de propulsion par réaction
F01D 25/00 - "MACHINES" OU MACHINES MOTRICES À DÉPLACEMENT NON POSITIF, p.ex. TURBINES À VAPEUR - Parties constitutives, détails ou accessoires non couverts dans les autres groupes ou d'un intérêt non traité dans ces groupes
This heat treatment apparatus has: a heat exchange unit that uses heat exchange between a first fluid and a second fluid, the heat exchange unit including a plurality of first channels for channeling the first fluid and a second channel for channeling the second fluid; a space-forming part having a space facing channel opening parts of each of the plurality of first channels; a first opening part provided to the space-forming part, the first opening part having a first opening; a rectifier disposed in the space of the space-forming part, the rectifier rectifying the first fluid; and an attachment part for detachably attaching the rectifier through the first opening. The space of the space-forming part is a space where there is a confluence of the first fluid flowing out from each of the channel opening parts, or a space through which the confluent first fluid flows into each of the channel opening parts. The rectifier faces each of the channel opening parts while being attached to the space-forming part.
F28F 9/02 - Boîtes de distribution; Plaques d'extrémité
F28F 3/08 - Eléments construits pour être empilés, p.ex. pouvant être séparés pour leur nettoyage
F28F 9/22 - Dispositions pour diriger les sources de potentiel calorifique dans des compartiments successifs, p.ex. aménagement des plaques de guidage
C07C 1/04 - Préparation d'hydrocarbures à partir d'un ou plusieurs composés, aucun d'eux n'étant un hydrocarbure à partir d'oxydes de carbone à partir de monoxyde de carbone avec de l'hydrogène
An ultrasonic flaw detection device 100 is provided with a transmission window 118, a transmission probe 110 for transmitting an ultrasonic beam from the transmission window 118 toward a pre-set range of an inspection surface of an inspection object in which inspection is necessary, a reception window 128 disposed in a relationship to the transmission window 118 whereby ultrasonic waves reflected outside the range in which inspection is necessary do not reach the reception window 128, and a reception probe 120 for receiving ultrasonic waves passing through the reception window 128.
G01N 29/22 - Recherche ou analyse des matériaux par l'emploi d'ondes ultrasonores, sonores ou infrasonores; Visualisation de l'intérieur d'objets par transmission d'ondes ultrasonores ou sonores à travers l'objet - Détails
G01N 29/32 - Dispositions pour supprimer des influences indésirables, p.ex. des variations de température ou de pression
This invention sets out a reaction device having a thermally conductive heat exchanger for causing, using heat exchange between a heat medium and a reaction fluid, a reaction of the reaction fluid to progress, the heat exchanger having therein a heat medium channel for channeling the heat medium and a reaction channel for channeling the reaction fluid. The reaction device has a heat transmission accelerator 53, which is provided in the heat medium channel and which is in close contact with the heat exchanger in order to accelerate the transmission of heat between the heat medium and the heat exchanger. The heat transmission accelerator is constituted by a collection of a plurality of types of partial heat transmission accelerators 53a. Replacing at least one of the partial heat transmission accelerators with a partial heat transmission accelerator of another type locally changes the heat transmission performance of the heat transmission accelerator, whereby the temperature distribution in the heat exchanger can be readjusted.
B01J 19/24 - Réacteurs fixes sans élément interne mobile
F28F 3/06 - Eléments ou leurs ensembles avec moyens pour augmenter la surface de transfert de chaleur, p.ex. avec des ailettes, avec des évidements, avec des ondulations les moyens pouvant être fixés sur l'élément
F28F 3/08 - Eléments construits pour être empilés, p.ex. pouvant être séparés pour leur nettoyage
A combustion gas supply system 1 comprises: an air compressor 3; a fuel supply device 5; a combustor 7 that generates pressurized combustion gas by burning fuel supplied by the fuel supply device and compressed air; a gas supply collection unit 9 for supplying the pressurized combustion gas to a calorie consumption device and collecting, as used gas, the pressurized combustion gas, the calories of which have been consumed; and a re-pressurizing compressor 11 that supplementally compresses part of the collected used gas so as to be supplied to the compressed air. The re-pressurizing compressor pressurizes the used gas so that the used gas has the same pressure as the compressed air, reuses the used gas, and discharges the residue of the used gas to outside.
This fiber-reinforced composite member molding device 1 comprises: a pair of molding dies 2, 3 that sandwich a prepreg laminated body P, said prepreg laminated body P being obtained by laminating a plurality of prepregs in which long carbon fibers are impregnated with a resin and the result is formed into sheet shapes; an induction heating coil 8 that heats a thermoplastic resin of the prepregs via the pair of molding dies 2, 3; and a cooling passage 9 that cools the resin via the molding dies 2, 3 after the resin has melted, wherein respective design surfaces 61, 71 of the molding dies 2, 3, said design surfaces coming into contact with the prepreg laminated body P, are segmented into a plurality of regions, a plurality of cells 62 that open along the design surfaces 61, 71 on the back side of the design surfaces 61, 71 are formed in the molding dies 2, 3 in accordance with the plurality of regions, the induction heating coil 8 is positioned in the cells 62, and the cooling passage 9 is formed along the respective design surfaces 61, 71 of the molding dies 2, 3. Sufficient rigidity is ensured in the molding dies, and temperature distribution during heating and cooling is regularized.
This fiber-reinforced composite member molding device comprises: a lower mold 2 that has a cavity 21; an upper mold 3 that has a core 31, between which core 31 and the cavity 21 a prepreg laminated body P is sandwiched; cartridge heaters 4 that heat the prepreg laminated body P via the lower mold 2 and the upper mold 3; and cooling medium passages 5 that cool the prepreg laminated body P via the lower mold 2 and the upper mold 3, wherein the lower mold 2 and the upper mold 3 come closer together to match the shrinkage of a thermoplastic resin of the prepreg laminated body P during cooling. Said fiber-reinforced composite member molding device is provided with a pin 11 that advances and retracts in the cavity 21, a cylinder 13 that causes the pin 11 to advance and retract in the cavity 21, and a control unit 6 that, during cooling, causes the pin 11 to advance into the cavity 21 and come into contact with the prepreg laminated body P, thereby adding pressure. A fiber-reinforced composite member that does not experience delamination at an end section of a prepreg laminated body with thick layers is thus molded and obtained without prolonging the molding time.
B29C 43/36 - Moules pour la fabrication d'objets de longueur définie, c. à d. d'objets séparés
B29C 33/02 - Moules ou noyaux; Leurs détails ou accessoires comportant des moyens incorporés de chauffage ou de refroidissement
B29C 43/18 - Moulage par pressage, c. à d. en appliquant une pression externe pour faire couler la matière à mouler; Appareils à cet effet pour la fabrication d'objets de longueur définie, c. à d. d'objets séparés en incorporant des parties ou des couches préformées, p.ex. moulage par pressage autour d'inserts ou sur des objets à recouvrir
B29C 43/54 - Dispositions pour compenser des changements de volume, p.ex. le retrait
64.
ELECTRIC TAXIING SYSTEM OF AIRCRAFT AND METHOD FOR CONTROLLING THE SYSTEM
An electric taxiing system of an aircraft (1) includes: a wheel (5a, 7a) of an aircraft (1); a taxiing motor (5b, 7b) which is rotated together with the wheel (5a, 7a) in landing of the aircraft (1) to apply breaking force to the wheel (5a, 7a) and to generate regenerative power according to the breaking force, and which rotates the wheel (5a, 7a) in taxiing of the aircraft (1); and a power supply control unit (27) which supplies the regenerative power to an electric element of the aircraft (1), the electric element (9b, 11b, 13b, 15b, 29a, 31a) being driven in order for the aircraft (1) to perform landing or re-takeoff after cancelling landing.
B64C 25/36 - Aménagements ou adaptations des roues, des pneumatiques ou des essieux
B60T 1/16 - Aménagements des éléments de freinage, c. à d. des parties de ceux-ci dans lesquelles se produit l'effet de freinage par action autre qu'en retardant les roues, p.ex. réaction par augmentation de la résistance de l'air, p.ex. par volets d'aérofreins
B64D 41/00 - Installations génératrices de puissance pour servitudes auxiliaires
H02P 3/18 - Dispositions pour l'arrêt ou le ralentissement de moteurs, génératrices électriques ou de convertisseurs dynamo-électriques pour arrêter ou ralentir individuellement un moteur dynamo-électrique ou un convertisseur dynamo-électrique pour arrêter ou ralentir un moteur à courant alternatif
B60T 8/17 - Utilisation de moyens de régulation électriques ou électroniques pour la commande du freinage
65.
FIBER REINFORCED COMPOSITE MEMBER MOLDING APPARATUS
Provided is a fiber-reinforced composite member molding device 1 that is provided with a lower mold 2 that has a cavity 21, an upper mold 3 that has a core 31 that mates with the cavity 21 of the lower mold 2 in a mold clamping state to sandwich a prepreg laminate P, and a heat source 10 that heats the prepreg laminate P through the lower mold 2 and upper mold 3, said device being used to mold a fiber-reinforced composite member by heating a resin of the prepreg laminate P between the lower mold 2 and the upper mold 3 by means of the heat source 10 and applying pressure, wherein a heat loss prevention portion 26 for the cavity is disposed in the lower mold 2, a heat loss prevention portion 36 for the core is disposed in the upper mold 3, heat can be prevented from escaping from the surroundings of the cavity of the upper mold and the core of the lower mold when heat is applied during molding, and as a result, a fiber-reinforced composite member with almost no defects such as wrinkles can be obtained.
Provided is a fiber-reinforced composite member forming device provided with: a pair of forming die parts 2, 3 which approach and separate from each other to sandwich, in a clamped state, a prepreg obtained by impregnating a resin into a plurality of laminated woven fabrics; and a heat source 4 for heating the prepreg resin via the pair of forming die parts 2, 3. Each of the pair of forming die parts 2, 3 is equipped with base dies 21, 33 and design dies 25, 35 that are detachably mounted on the base dies 21, 33 and come into contact with the pregpreg. The design dies 25, 35 in the pair of forming dies parts 2, 3 are made from a metal having a lower coefficient of thermal expansion than the base dies 21, 33, and by adopting a split structure in the forming die parts, it is possible to keep the effects expansion of the forming die parts due to heating has on the fiber-reinforced composite member during heating when forming low, after achieving a reduction in the burden on workers involved in replacing the forming die parts.
METHOD FOR DETECTING ARRANGEMENT DISORDER OF FIBERS IN CONDUCTIVE COMPOSITE MATERIAL, AND DEVICE FOR DETECTING ARRANGEMENT DISORDER OF FIBERS IN CONDUCTIVE COMPOSITE MATERIAL
In the present invention, a current can be made to flow in a conductive composite material by placing a coil 7 at a position facing the conductive composite material, thereby eliminating the need of work and so forth for affixing an electrode to the conductive composite material. As a result, disorder in the arrangement of fibers in the conductive composite material can easily be detected. Provided is a method for detecting meandering of fibers in a conductive composite material, the method including a step for placing a magnetic field sensor 8 at a position facing a surface Sa of a conductive composite material such that a magnetosensitive axis direction of the sensor is horizontal along the surface Sa and is parallel to a coil surface 7e. Therefore, a part where the arrangement of fibers is disordered in the conductive composite material can be detected by measuring the magnetic field with the magnetic sensor 8.
G01N 27/90 - Recherche ou analyse des matériaux par l'emploi de moyens électriques, électrochimiques ou magnétiques en recherchant des variables magnétiques pour rechercher la présence des criques en utilisant les courants de Foucault
A filler has a plurality of sheet materials arranged in parallel with a space therebetween. The sheet materials are used in a standing state, and a liquid is made to flow along the flat surfaces thereof. Each sheet material (F) has a plurality of support members (members M11 - M53) disposed such that the upper end of the uppermost support member corresponds to the upper end of the sheet material and the lower end of the lowermost support member corresponds to the lower end of the sheet material. Each of the support members has a pair of support walls parallel to the direction of flow and perpendicular to the flat surface of the sheet material, and a bridging part connecting the supporting walls. A sandwiching and holding structure that sandwiches and holds the sheet materials by at least one of the plurality of supporting members attached to one sheet material and at least one of the plurality of supporting members attached to an adjacent sheet material is formed, and the supporting members are positioned such that the sandwiching and holding structure extends in a linear shape through the plurality of sheet members.
B01J 19/32 - Eléments de remplissage en forme de grille ou d'éléments composés de plusieurs pièces pour constituer une unité ou un module dans l'appareil de transfert de chaleur ou de matière
B01D 3/26 - Colonnes de fractionnement dans lesquelles vapeur et liquide s'écoulent au contact l'un de l'autre, ou dans lesquelles le fluide est pulvérisé dans la vapeur, ou dans lesquelles un mélange de deux phases est admis à passer dans un seul sens
B01D 53/18 - Unités d'absorption; Distributeurs de liquides
B01J 10/00 - Procédés chimiques généraux faisant réagir un liquide avec des milieux gazeux autrement qu'en présence de particules solides; Appareillage spécialement adapté à cet effet
An aft section structure of a jet engine has an axis and the aft section structure is comprised of a casing defining a duct around the axis and opened axially fore and aft; a cone tapering aftward at a first angle with the axis and having a pointed end; one or more guide vanes, each of the vanes radially extending from the cone to the casing and comprising a pressure side at a second angle with a plane containing the axis; one or more spray bars, each of the spray bars extending radially within the duct and comprising one or more trailing sides, each of the trailing sides being directed aftward at a third angle with a plane containing the axis; and one or more flame holders, each of the flame holders extending radially within the duct and comprising one or more interior sides, each of the interior sides being directed aftward at a fourth angle with a plane containing the axis.
F02K 3/10 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant avec réchauffage supplémentaire du fluide de travail; Leur commande par postcombustion
F23R 3/18 - Moyens de stabilisation de la flamme, p.ex. accroche-flamme de postcombustion d'ensembles fonctionnels à propulsion par réaction
An end surface of each first side wall, an end surface of each first intermediate wall, and an end surface of each first regulating wall are joined, by diffusion bonding, to an adjacent second structure, and an end surface of each second side wall, an end surface of each second intermediate wall, and an end surface of each second regulating wall are joined, by diffusion bonding, to an adjacent first structure or a cover structure. The thickness dimension of the first side walls is greater than or equal to the thickness dimension of the first intermediate walls, and the thickness dimension of the second side walls is greater than or equal to the thickness dimension of the second intermediate walls.
B01J 19/24 - Réacteurs fixes sans élément interne mobile
C01B 3/38 - Production d'hydrogène ou de mélanges gazeux contenant de l'hydrogène par réaction de composés organiques gazeux ou liquides avec des agents gazéifiants, p.ex. de l'eau, du gaz carbonique, de l'air par réaction d'hydrocarbures avec des agents gazéifiants avec des catalyseurs
F28D 9/00 - Appareils échangeurs de chaleur comportant des ensembles de canalisations fixes en forme de plaques ou de laminés pour les deux sources de potentiel calorifique, ces sources étant en contact chacune avec un côté de la paroi d'une canalisation
F28F 3/00 - Eléments en forme de plaques ou de laminés; Ensembles d'éléments en forme de plaques ou de laminés
This reactor generates a product by reacting a raw material fluid by means of a heat exchange between the raw material fluid and a heating medium. The reactor is provided with a main reactor core and with a pre-reactor core. The main reactor core has: a main reaction flow path through which the raw material fluid is made to flow; and a main temperature-control flow path through which the heating medium is made to flow along the direction in which the raw material fluid flows inside the main reaction flow path. The pre-reactor core has: a pre-reaction flow path, an exit side of which communicates with an entrance side of the main reaction flow path, and through which the raw material fluid is made to flow; and a pre-temperature-control flow path, an entrance side of which communicates with an exit side of the main reaction flow path, and through which a product, as a heating medium, is made to flow along the direction in which the raw material fluid flows inside the pre-reaction flow path.
B01J 19/24 - Réacteurs fixes sans élément interne mobile
C01B 3/38 - Production d'hydrogène ou de mélanges gazeux contenant de l'hydrogène par réaction de composés organiques gazeux ou liquides avec des agents gazéifiants, p.ex. de l'eau, du gaz carbonique, de l'air par réaction d'hydrocarbures avec des agents gazéifiants avec des catalyseurs
F28D 9/00 - Appareils échangeurs de chaleur comportant des ensembles de canalisations fixes en forme de plaques ou de laminés pour les deux sources de potentiel calorifique, ces sources étant en contact chacune avec un côté de la paroi d'une canalisation
F28F 3/00 - Eléments en forme de plaques ou de laminés; Ensembles d'éléments en forme de plaques ou de laminés
[Problem] To provide a turbine that has a simple structure, that is composed of a CMC and achieves a wide range of gas flow passages while suppressing thermal stress acting on turbine stator blades, and that can consequently realize further improvement of performance and fuel consumption in jet engines. [Solution]A turbine stator blade 11 is composed of a CMC and has a shape in which a blade part 20, an outer band part 21 and an inner band part 22 are continuous; a front part 21b and a rear part 21c of the outer band part 21 of the turbine stator blade 11 are locked with a front locking part 12b and a rear locking part 12c of a hanger 12 composed of a metal material; and the hanger 12 is attached to a turbine case 2 composed of a metal material.
F01D 9/02 - Injecteurs; Logement des injecteurs; Aubes de stator; Tuyères de guidage
C04B 35/80 - Fibres, filaments, "whiskers", paillettes ou analogues
F01D 11/00 - Prévention ou réduction des pertes internes du fluide énergétique, p.ex. entre étages
F01D 25/00 - "MACHINES" OU MACHINES MOTRICES À DÉPLACEMENT NON POSITIF, p.ex. TURBINES À VAPEUR - Parties constitutives, détails ou accessoires non couverts dans les autres groupes ou d'un intérêt non traité dans ces groupes
F02C 7/00 - Caractéristiques, parties constitutives, détails ou accessoires non couverts dans, ou d'un intérêt plus général que, les groupes ; Entrées d'air pour ensembles fonctionnels de propulsion par réaction
A shield member (30) is disposed over a gap between platform portions (20) of adjacent turbine rotor blades (10) , made from a ceramic matrix composite, and configured to shield the gap between the platform portions (20) .
F01D 11/00 - Prévention ou réduction des pertes internes du fluide énergétique, p.ex. entre étages
C04B 35/80 - Fibres, filaments, "whiskers", paillettes ou analogues
F01D 25/00 - "MACHINES" OU MACHINES MOTRICES À DÉPLACEMENT NON POSITIF, p.ex. TURBINES À VAPEUR - Parties constitutives, détails ou accessoires non couverts dans les autres groupes ou d'un intérêt non traité dans ces groupes
F02C 7/28 - Agencement des dispositifs d'étanchéité
When a compressor vane or blade for an engine is used in an environment containing abundant foreign substances, deposits originated from the foreign substances are likely to deposit on surfaces of the vane. The compressor vane or blade according to the present disclosure has a base body of the compressor vane or blade; and a coating covering the base body, which consists essentially of one or more selected from the group of molybdenum disulfide and tungsten disulfide.
The present invention generates a level difference between a metal sheath and a coating material layer formed on a blade face of a blade main body. This coating device comprises: a jig (10) that supports a guide vane (V) which has a metal sheath (S) covering a leading edge section (LE); a nozzle (4) that sprays a coating material to a vane main body (Va); a robot (5) that moves the nozzle; and a control unit (6) that controls spraying operations of the nozzle (4) and the robot (5). The jig (10) includes: a movable covering body (15) that covers the metal sheath (S) so as to be separable therefrom and covers an adhesive exposed section (Ta) between the side rim section (Sr) of the metal sheath (S) and the blade face (Vd) of the vane main body (Va); and a covering-body driving unit (20) that moves the movable covering body (15) between a state where the movable covering body (15) covers the metal sheath (S) and a state where the movable covering body (15) is separated from the metal sheath (S) while covering the metal sheath (S). The control unit (6) performs control of shifting from a sheath-covering coating mode to a finishing coating mode.
B05B 12/20 - Aménagements de commande de la distribution; Aménagements de réglage de l’aire de pulvérisation pour régler l’aire de pulvérisation Éléments de masquage, c. à d. éléments définissant des aires non revêtues sur un objet à revêtir
F01D 5/28 - Emploi de matériaux spécifiés; Mesures contre l'érosion ou la corrosion
F01D 25/00 - "MACHINES" OU MACHINES MOTRICES À DÉPLACEMENT NON POSITIF, p.ex. TURBINES À VAPEUR - Parties constitutives, détails ou accessoires non couverts dans les autres groupes ou d'un intérêt non traité dans ces groupes
F02C 7/00 - Caractéristiques, parties constitutives, détails ou accessoires non couverts dans, ou d'un intérêt plus général que, les groupes ; Entrées d'air pour ensembles fonctionnels de propulsion par réaction
F02C 7/30 - Prévention de la corrosion dans les espaces balayés par les gaz
A case body (5a) of a fan case (5) in a jet engine (3) is formed by use of a composite material of carbon fiber reinforced plastic. Metal rings (5b, 5c) are respectively attached to a leading edge and a trailing edge of the case body (5a). The metal rings (5b, 5c) are electrically connected together by a conductive cable (5d). Both of the metal rings (5b, 5c) and the conductive cable (5d) constitute a path of a lightning current.
F02K 3/06 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant dans lesquels une partie du fluide énergétique passe en dehors de la turbine et de la chambre de combustion l'ensemble fonctionnel comprenant des soufflantes carénées, c. à d. des soufflantes à fort débit volumétrique sous basse pression pour augmenter la poussée, p.ex. du type à double flux comprenant une soufflante avant
B64D 29/06 - Fixation des nacelles, carénages ou capotages
B64D 45/02 - Dispositifs de protection contre la foudre; Déperditeurs de potentiel
F02C 7/00 - Caractéristiques, parties constitutives, détails ou accessoires non couverts dans, ou d'un intérêt plus général que, les groupes ; Entrées d'air pour ensembles fonctionnels de propulsion par réaction
F04D 29/54 - Moyens de guidage du fluide, p.ex. diffuseurs
A compressor vane or blade for an engine used in an environment containing abundant foreign substances is provided which comprises: a base body of the compressor vane or blade; and a coating consisting of a nitride of titanium beyond 60 at% but less than 85 at% and a balance of silicon.
F04D 29/32 - Rotors spécialement adaptés aux fluides compressibles pour pompes à flux axial
F02C 7/00 - Caractéristiques, parties constitutives, détails ou accessoires non couverts dans, ou d'un intérêt plus général que, les groupes ; Entrées d'air pour ensembles fonctionnels de propulsion par réaction
F04D 29/70 - Grilles d'aspiration; Filtres; Séparateurs de poussière; Nettoyage
C23C 14/06 - Revêtement par évaporation sous vide, pulvérisation cathodique ou implantation d'ions du matériau composant le revêtement caractérisé par le matériau de revêtement
78.
METHOD AND APPARATUS FOR CONTROLLING INLET TEMPERATURE OF DEDUSTING APPARATUS IN OXYGEN COMBUSTION BOILER EQUIPMENT
A combustion-support-gas bypass line 12 is provided to cause combustion support gas to bypass a preheater 4. A combustion-support-gas flow control damper 13 is provided in the combustion-support-gas bypass line 12. An inlet temperature 14a of a deduster 6 is measured by a temperature sensor 14 and the inlet temperature 14a measured by the temperature sensor 14 is inputted to a controller 15 and is compared with a set temperature at least equal to an acid dew-point preliminarily set in the controller 15. On the basis of a comparison result, an opening-degree control signal 13a is outputted from the controller 15 to the combustion-support-gas flow control damper 13 so as to make the inlet temperature 14a to a set temperature at least equal to an acid dew-point.
F23J 15/00 - Aménagement des dispositifs de traitement de fumées ou de vapeurs
F23C 9/00 - Appareils à combustion caractérisés par des dispositions pour renvoyer les produits de combustion ou les gaz de fumée dans la chambre de combustion
F23C 99/00 - Matière non prévue dans les autres groupes de la présente sous-classe
F23L 7/00 - Alimentation du foyer en liquides ou gaz non combustibles autres que l'air, p.ex. oxygène, vapeur d'eau
79.
STATOR-VANE STRUCTURE AND TURBOFAN ENGINE EMPLOYING THE SAME
[Problem] To provide a stator-vane structure with which it is possible to suppress a pressure loss caused by a gap or a level difference between liners, while forming an air channel by using stator vanes made of a composite material and the liners in a turbofan engine, and to provide a turbofan engine employing this stator-vane structure. [Solution] Inner liners (40) are made to abut each other so as to clamp therebetween a vane base section (21) of a fan- outlet guide vane (stator vane) (20) made of a composite material, outer liners (50) are made to abut each other so as to clamp therebetween a vane tip section (22) of the fan-outlet guide vane (20), and division lines (45, 46, 55, 56) that are formed between the liners on the leading-edge side are made to extend along streamline directions.
F02K 3/06 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant dans lesquels une partie du fluide énergétique passe en dehors de la turbine et de la chambre de combustion l'ensemble fonctionnel comprenant des soufflantes carénées, c. à d. des soufflantes à fort débit volumétrique sous basse pression pour augmenter la poussée, p.ex. du type à double flux comprenant une soufflante avant
F01D 9/04 - Injecteurs; Logement des injecteurs; Aubes de stator; Tuyères de guidage formant une couronne ou un secteur
F02C 7/00 - Caractéristiques, parties constitutives, détails ou accessoires non couverts dans, ou d'un intérêt plus général que, les groupes ; Entrées d'air pour ensembles fonctionnels de propulsion par réaction
When a combination of a vane type of a stator vane and a vane type of a stator vane for one straightening plate is the same as a combination of a vane type of a stator vane and a vane type of a stator vane for the other straightening plate, positions of the first straightening plate side connection portions and the second straightening plate side connection portions of the one straightening plate and the other straightening plate are the same as each other. When the combinations are different from each other, at least one of the positions of the first straightening plate side connection portions of the one straightening plate and the other straightening plate and the positions of the second straightening plate side connection portions of the one straightening plate and the other straightening plate are different from each other.
F02K 3/06 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant dans lesquels une partie du fluide énergétique passe en dehors de la turbine et de la chambre de combustion l'ensemble fonctionnel comprenant des soufflantes carénées, c. à d. des soufflantes à fort débit volumétrique sous basse pression pour augmenter la poussée, p.ex. du type à double flux comprenant une soufflante avant
F01D 9/02 - Injecteurs; Logement des injecteurs; Aubes de stator; Tuyères de guidage
F02K 3/00 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant
F04D 29/54 - Moyens de guidage du fluide, p.ex. diffuseurs
A debris removal device (1) includes: an end mass (2) adapted to be capable of approaching debris (X) to be removed; a debris capture device (3) separably- mounted on the end mass (2); and a tether (4) connecting the debris capture device (3) and the end mass (2) to each other. The debris capture device (3) includes a harpoon (31) capable of penetrating into the debris (X), a shooting device (32) for shooting the harpoon (31), a guide member (33) positioned to be capable of coming into contact with the surface of the debris (X) to adjust the shooting angle of the harpoon (31) with respect to the surface of the debris (X), and a switch (34) that sends the shooting signal to the shooting device (32). The debris removal device (1) is configured such that, after the harpoon (31) is penetrated into the debris (X), the end mass (2) is separated from the debris capture device (3), and the tether (4) is released into outer space.
An image analysis apparatus, image analysis method, and program capable of easily analyzing orientations of fiber bundles from a three-dimensional image of a CMC is proposed. [Solution] An image analysis apparatus for analyzing orientations of fiber bundles of X-yarns and Y-yarns from a three-dimensional image of a woven fabric made of fiber bundles of the X-yarns, the Y-yarns, and Z-yarns includes: a binarization unit that binarizes the three-dimensional image; an overlapping area extraction unit that extracts an overlapping area, in which the X-yarns and the Y-yarns perpendicularly and three-dimensionally intersect with each other, from the binarized image; a reference direction determination unit that averages an overlapping direction of each voxel included in the overlapping area and determines the averaged direction as a reference direction; a Z-yarn removal unit that removes the Z-yarns from the binarized image by applying a directional distance method on a reference plane perpendicular to the reference direction; and a fiber bundle orientation estimation unit that applies the directional distance method again to the image, from which the Z-yarns have been removed, on the reference plane and estimates the orientations of the fiber bundles of the X-yarns and the Y-yarns on the basis of a directional distance calculated upon the application.
G01N 23/046 - Recherche ou analyse des matériaux par l'utilisation de rayonnement [ondes ou particules], p.ex. rayons X ou neutrons, non couvertes par les groupes , ou en transmettant la radiation à travers le matériau et formant des images des matériaux en utilisant la tomographie, p.ex. la tomographie informatisée
D06H 3/08 - Visite des matériaux textiles par moyens photo-électriques ou par télévision
Heat exchangers (17, 31) are adjacent to electric driving units (19, 33). Electric blowers of electric blower units (21, 35) rotate at rotational speed corresponding to amounts of heat generation of the electric driving units (19, 33) and suck air (ventilation air and outboard air). The sucked-in air passes through the heat exchangers (17, 31) that are adjacent to the electric driving units (19, 33).
B64D 13/00 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacement réservé au fret
H05K 7/20 - Modifications en vue de faciliter la réfrigération, l'aération ou le chauffage
84.
COOLING APPARATUS FOR COOLING ELECTRONIC DEVICE IN AIRCRAFT
A cooling device applicable to an airplane having a pressurized cabin and a ram air channel (13) for cooling an electronic device (11) arranged in the pressurized cabin, is comprised of a partition wall (15) separating the pressurized cabin from the ram air channel (15); and a heat exchanger (21) thermally in contact with the electronic device and exposed to the ram air channel so as to radiate heat to a ram air.
A method of manufacturing a Ni alloy part formed by metal powder injection molding includes a step of solution treating a sintered compact, which is obtained by sintering and molding a precipitation hardening Ni alloy powder by metal injection molding, by allowing the sintered compact to hold at 1050°C -1250°C for 1 - 5 hours, followed by rapidly cooling to room temperature, where the precipitation hardening Ni alloy powder includes 0.65% - 1.15 mass % of Ti, 0.20% - 0.80 mass % of Al, 17.00% - 21.00 mass % of Cr, 4.75% - 5.50 mass % Nb, 2.80% - 3.30 mass % of Mo, 50.00% - 55.00 mass % of Ni, and the balance including Fe and unavoidable impurities, and a step of aging- treating the solution-treated sintered compact by allowing the solution-treated sintered compact to hold at 600°C - 800°C, followed by cooling to room temperature.
C22F 1/10 - Modification de la structure physique des métaux ou alliages non ferreux par traitement thermique ou par travail à chaud ou à froid du nickel ou du cobalt ou de leurs alliages
B22F 3/24 - Traitement ultérieur des pièces ou objets
B22F 5/04 - Fabrication de pièces ou d'objets à partir de poudres métalliques caractérisée par la forme particulière du produit à réaliser d'aubes de turbines
C22C 19/05 - Alliages à base de nickel ou de cobalt, seuls ou ensemble à base de nickel avec du chrome
F01D 25/00 - "MACHINES" OU MACHINES MOTRICES À DÉPLACEMENT NON POSITIF, p.ex. TURBINES À VAPEUR - Parties constitutives, détails ou accessoires non couverts dans les autres groupes ou d'un intérêt non traité dans ces groupes
F02C 7/00 - Caractéristiques, parties constitutives, détails ou accessoires non couverts dans, ou d'un intérêt plus général que, les groupes ; Entrées d'air pour ensembles fonctionnels de propulsion par réaction
A stator vane arranged around an axis to form a turbine nozzle is comprised of: an airfoil section elongated in a radial direction relative to the axis; an outer band section continuous to an outer end of the airfoil section and bent in a circumferential direction relative to the axis; a first hook section continuous to a leading end in the axial direction of the outer band section and bent outward in the radial direction; a second hook section continuous to a trailing end in the axial direction of the outer band section and bent outward in the radial direction; an inner band section continuous to an inner end of the airfoil section and bent in the circumferential direction; a flange section continuous to an end in the axial direction of the inner band section and bent inward in the radial direction; and a reinforcement fiber fabric continuous throughout the airfoil section, the outer band section, the first hook section, the second book section, the inner band section and the flange section and unitized with a ceramic.
F01D 9/02 - Injecteurs; Logement des injecteurs; Aubes de stator; Tuyères de guidage
C04B 35/80 - Fibres, filaments, "whiskers", paillettes ou analogues
F01D 25/00 - "MACHINES" OU MACHINES MOTRICES À DÉPLACEMENT NON POSITIF, p.ex. TURBINES À VAPEUR - Parties constitutives, détails ou accessoires non couverts dans les autres groupes ou d'un intérêt non traité dans ces groupes
F02C 7/00 - Caractéristiques, parties constitutives, détails ou accessoires non couverts dans, ou d'un intérêt plus général que, les groupes ; Entrées d'air pour ensembles fonctionnels de propulsion par réaction
A non-destructive inspection apparatus (1) according to the present invention non-destructively inspects a joining area of a substrate (A1) comprising a fiber-reinforced material and a joining material (A2) comprising a metal material in a gas turbine engine component (A) formed through the joining of the joining material to the metal material. The non-destructive inspection apparatus (1) is provided with a movement apparatus (3) for moving the gas turbine engine component, a light source device (4) for emitting laser light (L), an infrared imaging device (5) for imaging the gas turbine engine component in a state of being irradiated with the laser light, and a control and calculation processing device (8) for storing shape data for the gas turbine engine component, controlling the movement apparatus on the basis of the shape data so that laser light is irradiated onto the joining area, and obtaining a result indicating the state of the joining area on the basis of the imaging data obtained by the infrared imaging device.
A thrust increasing device (10) includes: a fuel injector (10b) that ejects fuel toward a jet flow; an ignition device (10c) that is disposed downstream from the fuel injector; a cylindrical duct (10a) that surrounds a combustion region; a flame holder (10d) that is disposed in the duct; and a swirling flow generating part (10d) that maintains an axial (L) flow of the jet flow in an axial direction of the duct in an outer region of the duct in a radial direction inside the duct and that converts the jet flow to a swirling flow centered on an axis of the duct in an inner region of the duct in the radial direction inside the duct.
F02K 1/28 - Ensembles fonctionnels caractérisés par la forme ou la disposition de la tubulure de jet ou de la tuyère; Tubulures de jet ou tuyères particulières à cet effet utilisant des jets de fluide pour influencer l'écoulement du jet
F02C 7/00 - Caractéristiques, parties constitutives, détails ou accessoires non couverts dans, ou d'un intérêt plus général que, les groupes ; Entrées d'air pour ensembles fonctionnels de propulsion par réaction
F02K 1/38 - Introduction d'air à l'intérieur du jet
F02K 1/78 - Autres structures des tubulures de jet
F02K 3/10 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant avec réchauffage supplémentaire du fluide de travail; Leur commande par postcombustion
F23R 3/18 - Moyens de stabilisation de la flamme, p.ex. accroche-flamme de postcombustion d'ensembles fonctionnels à propulsion par réaction
A dynamic system estimation device and method, whereby estimation for more performance parameters than there are sensors can be performed, said estimation taking temporal changes into account. The dynamic system estimation device includes: a prescribed number of sensors that detect prescribed observation values from a gas turbine engine; and a Kalman filter that uses a dynamic model of the gas turbine engine and estimates the state of the gas turbine engine, on the basis of the observation values detected by the sensors. The gas turbine engine includes an element having changes in temporal performance recorded by performance parameters. The Kalman filter enables more than the prescribed number of performance parameters to be estimated, as a result of introducing a first-order lag element in place of said element.
F02C 7/00 - Caractéristiques, parties constitutives, détails ou accessoires non couverts dans, ou d'un intérêt plus général que, les groupes ; Entrées d'air pour ensembles fonctionnels de propulsion par réaction
F01D 25/00 - "MACHINES" OU MACHINES MOTRICES À DÉPLACEMENT NON POSITIF, p.ex. TURBINES À VAPEUR - Parties constitutives, détails ou accessoires non couverts dans les autres groupes ou d'un intérêt non traité dans ces groupes
G05B 13/04 - Systèmes de commande adaptatifs, c. à d. systèmes se réglant eux-mêmes automatiquement pour obtenir un rendement optimal suivant un critère prédéterminé électriques impliquant l'usage de modèles ou de simulateurs
The present embodiment improves the durability of an afterburner 25 and yet suppresses a reduction in the engine efficiency of an aircraft engine 1. A ring-shaped cooling channel 35 through which cooling air CA flows is formed between the outer peripheral surface of a liner 31 and the inner peripheral surface of a rear duct 29. A plurality of cooling holes 37 for blowing the cooling air CA along the inner peripheral surface of the liner 31 are formed penetrating the liner 31. A ring-shaped annulus flame-holding member 51 on the inner peripheral surface of the liner 31 is provided concentrically with respect to a plurality of radial flame-holding members 47. The inner diameter of the annulus flame-holding member 51 decreases in the downstream direction. The annulus flame-holding member 51 functions as a throttle ring which throttles the flowing of a main flow of a mixed gas inside the liner 31.
F02K 3/10 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant avec réchauffage supplémentaire du fluide de travail; Leur commande par postcombustion
F23R 3/20 - Moyens de stabilisation de la flamme, p.ex. accroche-flamme de postcombustion d'ensembles fonctionnels à propulsion par réaction comprenant des moyens d'injection du combustible
The present invention sufficiently ensures the ignition stability and the flame-holding property of an afterburner (25) while suppressing a reduction in the engine efficiency of an aircraft engine (1). A flame holder (45) is disposed directly downstream of an injection hole (41) of a fuel injector (39) in a liner (31). The flame holder (45) comprises: a ring-shaped annulus flame-holding member (49) which is provided on the inner circumferential surface of the liner (31) and is capable of propagating a flame in the circumferential direction; and a plurality of radial flame-holding members (51) which are radially disposed inwards of the annulus flame-holding member (49) and are capable of propagating the flame in the radial direction. A guide ring (53) is provided inwards of the radial flame-holding members (51), and a ring-shaped guide channel (57) that guides a fuel-containing mixed gas in the downstream direction is formed between the outer peripheral surface of the guide ring (53) and the inner peripheral surface of the annulus flame-holding member (49).
F02K 3/10 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant avec réchauffage supplémentaire du fluide de travail; Leur commande par postcombustion
F23R 3/20 - Moyens de stabilisation de la flamme, p.ex. accroche-flamme de postcombustion d'ensembles fonctionnels à propulsion par réaction comprenant des moyens d'injection du combustible
92.
DESULFURIZATION APPARATUS AND EXHAUST GAS PROCESSING SYSTEM USING THE SAME
Provided are: a desulfurization apparatus employing a limestone-gypsum method, which has excellent economic efficiency and does not undergo troubles that may be caused by flying particles; and an exhaust gas treatment system, whereby it becomes possible to collect high-purity carbon dioxide. The desulfurization apparatus is equipped with: a desulfurization unit for bringing an absorption solution containing a calcium compound into contact with an exhaust gas to remove a sulfur oxide from the exhaust gas; a removal unit for removing gypsum, which is generated from the sulfur oxide, from the absorption solution; and a washing unit for washing the exhaust gas, which has contacted with the adsorption solution, using the adsorption solution from which gypsum has been removed as a washing solution, thereby removing calcium-containing particles contained in the exhaust gas. In the removal unit, the gypsum is sorted into larger gypsum grains and smaller gypsum grains using a cyclone separator, the adsorption solution containing the larger gypsum grains is filtrated, and the resultant filtrate is supplied to the washing section. The exhaust gas treatment system is equipped with the desulfurization apparatus, a denitration apparatus and a carbon dioxide collection apparatus, wherein a portion of a collected gas that is discharged from the carbon dioxide collection apparatus is supplied to the removal unit in the desulfurization apparatus as an oxygen source.
B01D 33/04 - Filtres avec éléments filtrants mobiles au cours de l'opération de filtration à bandes filtrantes ou analogues supportées par des cylindres imperméables pour la filtration
A composite wing equipped with a composite-wing body (11) which is obtained by molding and comprises a composite material comprising strengthening fibers and a thermoplastic resin or heat-curable resin, and further equipped with a metal sheath (12) for covering a leading edge section (11A) and joined, via a film adhesive (13) obtained by impregnating a mesh with a hard adhesive, to the leading edge section (11A), which includes the leading edge (11a) of the composite-wing body (11) and the wing surface (11b) in the vicinity thereof, wherein the leading edge (11a) of the leading edge section (11A) of the composite-wing body (11) is provided with notched sections (11d) which do not require leading-edge (R) finishing and are formed during a step for removing surplus-material sections (15, 16) which remain on the leading edge (11a) after molding. As a result, it is possible to reduce production costs and shorten production time.
F01D 9/02 - Injecteurs; Logement des injecteurs; Aubes de stator; Tuyères de guidage
F01D 25/00 - "MACHINES" OU MACHINES MOTRICES À DÉPLACEMENT NON POSITIF, p.ex. TURBINES À VAPEUR - Parties constitutives, détails ou accessoires non couverts dans les autres groupes ou d'un intérêt non traité dans ces groupes
F02C 7/00 - Caractéristiques, parties constitutives, détails ou accessoires non couverts dans, ou d'un intérêt plus général que, les groupes ; Entrées d'air pour ensembles fonctionnels de propulsion par réaction
F04D 29/54 - Moyens de guidage du fluide, p.ex. diffuseurs
A device that carries out vacuum processing on a reinforced fiber is provided with: a chamber that maintains its entirety in a reduced pressure state; a feed roller disposed so as to make the reinforced fiber hang down into the chamber; a processing machine disposed in the chamber through which the reinforced fiber dropped down from the feed roller passes; a capture device that captures the tip of the reinforced fiber passing through the processing machine and dropped vertically and is disposed for positioning; and uptake bobbin constituted to take up the reinforced fiber that has been processed by the processing machine; and a flexible cord for coming into contact with the reinforced fiber from a first position surrounding the tip that has been positioned by the capture device and pulling to a second position guided to the uptake bobbin in synchrony with the uptake bobbin.
A method of manufacturing packing includes: a main condition determination step (Step 1) of determining types of a gas and a liquid which are brought into gas-liquid contact and a main plate (11) to be used; a numerical analysis step (Step 2) of calculating a relationship between a contact angle (.theta.s) and a liquid film length ratio (Lw/Lt) ; a rib arrangement determination step (Step 3) of determining the arrangement (intervals) of a rib (12) ; a rib condition determination step (Step 4) of determining rib conditions; a rib property determination step (Step 5) of calculating the minimum value (Lrmin) of the flow direction length of the rib (12) satisfying the contact angle (.theta.s) and a strength requirement; a minimum value condition confirmation step (Step 6) of confirming whether or not a liquid film length (Lw (.theta.s) ) is greater than the minimum value (Lrmin) ; and a rib length determination step (Step 7) of determining the flow direction length (Lr) of the rib (12) within a range from the minimum value (Lrmin) to the liquid film length (Lw (.theta.s) ) .
B01J 19/32 - Eléments de remplissage en forme de grille ou d'éléments composés de plusieurs pièces pour constituer une unité ou un module dans l'appareil de transfert de chaleur ou de matière
B01D 53/18 - Unités d'absorption; Distributeurs de liquides
A mixed gas containing a precursor gas, an additive gas and a carrier gas is supplied to a preform (100) stored in an electric fiirnace (10), and silicon carbide is deposited by chemical vapor deposition or chemical vapor phase impregnation to form a film. The preform (100) includes multiple fiber bundles, and the fiber bundles include multiple fibers. This heat-resistant composite material includes a ceramic fiber preform impregnated with silicon carbide, and producing the composite material involves a step in which silicon carbide is deposited between the fibers to integrate the fibers which configure the fiber bundles, and a step in which silicon carbide is deposited between the fiber bundles to integrate the fiber bundles. Hereby, uniformity of embedding and growth rate of the silicon carbide film are both attained.
In the present embodiment, in the production of a heat-resistant composite material resulting from impregnating a ceramic fiber preform with silicon carbide, a mixed gas containing starting material gas, an additive gas, and a carrier gas is supplied to a substrate (100) having a minute structure such as a preform stored in an electric furnace (10), silicon carbide is deposited to form a film by means of a chemical vapor deposition method or a chemical vapor infiltration method, and the film formation growth speed and embedding uniformity are controlled by means of the amount of additive gas added to the starting material gas, the starting material gas contains tetramethylsilane , and the additive gas contains a molecule containing chlorine such as methyl chloride or hydrogen chloride. The film formation growth speed and embedding uniformity of the silicon carbide are both achieved.
A connection supporting body (33), which comprises a pair of divided pieces (34, 34) joined to a vane base end part (21) from either side in the vane thickness direction, is disposed at a part where the vane base end part (21) of a guide vane (20) and mounting flanges (31f) are connected together; elongated protrusions (21a) are formed on either side of the vane base end part (21); engagement grooves (35a), which engage with the elongated protrusions (21a) formed on the vane base end part (21), are formed in the pair of divided pieces (34, 34) of the connection supporting body (33); respective side edges (35b, 35b) of the pair of divided pieces (34, 34), which are located on the center side of the vane and extend along the vane chord direction, are formed so as to rise toward the center of the vane; the tips of the side edges (35b, 35b) are chamfered; and the vane base end part (21) is held between the pair of divided pieces (34, 34) of the connection supporting body (33) by a fastening force which is applied from either side in the vane width direction by the pair of divided pieces (34, 34) of the connection supporting body (33). The occurrence of a problem of peeling-off of a reinforced fiber layer at the end part of the vane made of a composite material can be minimized.
A fan case is provided with: a cylindrical case main body (10) comprising a composite material; a linking ring (20) made of Al, the linking ring (20) being fittably secured to the rear end of the case main body (10) and being provided with an annular groove (21) for receiving a reverse thrust load from a reverse-thrust-force-transmitting body (8); and a ring construct (30) made of a Ti alloy, the ring construct (30) being arranged on the rear end of the case main body (10) and being provided with an arcuate groove (31) for receiving and holding a greater reverse thrust load than the reverse thrust load received by the linking ring (20). The ring construct (30) is fitted into an incision (22) in the linking ring (20), and is brought in contact with an outward receiving wall (23) of the linking ring (20), whereby the ring construct (30) is positioned along an axial center (CL) direction and a radial direction relative to the case main body (10), and the annular groove (21) and the arcuate groove (31) are continuous with each other. The ring construct made of a Ti alloy for receiving a great reverse thrust load can be arranged with high positioning accuracy, and can be made to receive and hold the reverse thrust load without imbalance.
F01D 25/00 - "MACHINES" OU MACHINES MOTRICES À DÉPLACEMENT NON POSITIF, p.ex. TURBINES À VAPEUR - Parties constitutives, détails ou accessoires non couverts dans les autres groupes ou d'un intérêt non traité dans ces groupes
F01D 25/24 - Carcasses d'enveloppe; Eléments de la carcasse, p.ex. diaphragmes, fixations
F02C 7/00 - Caractéristiques, parties constitutives, détails ou accessoires non couverts dans, ou d'un intérêt plus général que, les groupes ; Entrées d'air pour ensembles fonctionnels de propulsion par réaction
F02K 3/02 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant dans lesquels une partie du fluide énergétique passe en dehors de la turbine et de la chambre de combustion
A low-pressure turbine (1) for a jet engine, said turbine being equipped with a turbine case (2), turbine blades (3) that rotate about the axis of the turbine case (2), and a shroud (4) that comprises multiple shroud segments (4A) arranged annularly along the inner peripheral surface of the turbine case (2) so as to surround the turbine blades (3), wherein an elongated protrusion (4a) and an outward groove (4b) are formed on each shroud segment (4A), each shroud segment (4A) is fixed to the turbine case (2) by engaging the elongated protrusion (4a) with a receiving groove (2a) of the turbine case (2) in the axial direction and by engaging the outward groove (4b) with an inward elongated protrusion (2b) of the turbine case (2), and each shroud segment (4A) has a pressure-receiving part (4e) formed thereon for receiving a force for releasing the engagement state of the outward groove (4b) with the inward elongated protrusion (2b) of the turbine case (2) when removing the shroud segment (4A) from the turbine case (2). The present invention enables disassembling work to be easily performed while achieving reduction of engine performance loss and reduction of thermal fatigue of the turbine case.
F01D 11/08 - Prévention ou réduction des pertes internes du fluide énergétique, p.ex. entre étages pour obturations de l'espace entre extrémités d'aubes du rotor et stator
F01D 9/04 - Injecteurs; Logement des injecteurs; Aubes de stator; Tuyères de guidage formant une couronne ou un secteur
F01D 25/00 - "MACHINES" OU MACHINES MOTRICES À DÉPLACEMENT NON POSITIF, p.ex. TURBINES À VAPEUR - Parties constitutives, détails ou accessoires non couverts dans les autres groupes ou d'un intérêt non traité dans ces groupes
brevets
