A device for driving at least one wheel of an aircraft landing gear is provided. The device includes at least one wheel having a rim, an electric motor having a shaft, and a mechanical transmission system for mechanical transmission between the shaft of the motor and the rim. The mechanical transmission system includes a mechanical reduction gear. The mechanical reduction gear includes a sun gear secured in rotation to the shaft and having an external toothing, a stationary ring gear with internal toothing, a movable ring gear secured in rotation to the rim and having an internal toothing, and planet gears that are meshed with the sun gear and each have two external toothing meshed respectively with the toothing of the stationary and movable ring gears.
An accessory gearbox houses at least one gear train with a series of pinions. The casing has two substantially flat and opposite parallel side walls between which are mounted support shafts for each of the pinions, each of which receives accessories, and which define in the enclosure an internal volume surrounding a shaft supporting at least one hybridization pinion. The gearbox receives at least one electric machine having a rotor and a stator, wherein the rotor of the electric machine is supported by the shaft supporting the hybridization pinion of the gear train, and the stator extends around the rotor in the internal volume.
F16H 57/021 - Shaft support structures, e.g. partition walls, bearing eyes, casing walls or covers with bearings
F02C 7/32 - Arrangement, mounting, or driving, of auxiliaries
F16H 1/22 - Toothed gearings for conveying rotary motion without gears having orbital motion involving more than two intermeshing members with arrangements for dividing torque between two or more intermediate shafts
3.
DEVICE FOR DRIVING AT LEAST ONE WHEEL OF AN AIRCRAFT LANDING GEAR
A device for driving at least one wheel of an aircraft landing gear including at least one landing gear wheel, this wheel including a rim, an electric motor including a shaft, a mechanical transmission system between the shaft of the motor and the rim, this mechanical transmission system including a mechanical reducer including a sun gear secured in rotation to the shaft of the motor, a ring gear, and planet gears which are carried by a planet carrier and which each includes three external toothings, including a median external toothing which is meshed with a toothing of the sun gear, and two lateral external toothings which are respectively meshed with toothings of the ring gear.
B64C 25/32 - Alighting gear characterised by elements which contact the ground or similar surface
B64C 25/34 - Alighting gear characterised by elements which contact the ground or similar surface wheeled type, e.g. multi-wheeled bogies
F16H 1/24 - Toothed gearings for conveying rotary motion without gears having orbital motion involving gears essentially having intermeshing elements other than involute or cycloidal teeth
4.
SPEED REDUCER FOR A DEVICE FOR DRIVING A WHEEL OF AN AIRCRAFT LANDING GEAR
A mechanical speed reducer, in particular for a device for driving at least one wheel of an aircraft landing gear, this reducer including a first sun gear including external toothing, first planet gears meshed with the external toothing of the first sun gear, these first planet gears being carried by a first planet carrier, a stationary ring gear meshed with the planet gears, and second planet gears meshed with a ring gear and with an external toothing of said first planet carrier, these second planet gears being carried by a second planet carrier.
A planet carrier for a speed reducer of an aircraft turbomachine, the planet carrier including a cage carrier and a cage. The cage can have two parts: a first part having a wall and bridges, these bridges projecting axially from a face of this wall and including first axial ends connected to this face and second free axial ends; and a second part having another of the walls, this other wall including a face to which the free ends of the bridges are applied. The two parts of the cage can be attached together by screws.
A drive assembly for a mechanical reducer for a turbomachine, in particular for an aircraft, includes planet gears, a planet carrier having at least one transverse wall, plain bearings for guiding the planet gears in rotation, and an oil supply circuit for the plain bearings. The planet carrier has collars for attaching the planet gears to the at least one transverse wall, and each of the planet gears includes at least one external cylindrical surface for forming an oil film with an internal cylindrical surface portion of each of the collars for forming said oil film.
A plain bearing for a mechanical reducer for a turbomachine is integrally formed and includes a cylindrical body. The cylindrical body has an external cylindrical guide surface, a first axial mounting extension, a first circumferential edge extending around the first extension, a second axial mounting extension, and a second circumferential edge extending around the second extension. The plain bearing further includes an attachment cover connected to the first axial extension and extending axially opposite said first edge.
An aircraft turbomachine including a mechanical reduction gear including one sun gear, a ring gear, planet gears which are meshed with the sun gear and the ring gear, each planet gear including a first toothing for meshing with the sun gear, and a second toothing for meshing with the ring gear, the first toothing of each planet gear having a diameter greater than that of the second toothing of the planet gear, and a planet carrier, wherein the sun gear is coupled to a first rotor shaft of the turbomachine, the planet carrier is coupled to a second rotor shaft of the turbomachine, the ring gear is fixed to a stator of the turbomachine.
A propulsion assembly for an aircraft comprising at least two electric motors configured to be disposed in a wing of the aircraft and each comprising a rotor having a motor shaft movable about a motor axis, at least one propeller borne by a propeller shaft movable about a propeller axis and mechanically coupled to the motor shaft of the at least two electric motors, the propeller axis being perpendicular to the motor axis of the at least two electric motors.
B64D 35/08 - Transmitting power from power plant to propellers or rotors; Arrangements of transmissions characterised by the transmission being driven by a plurality of power plants
B64D 27/24 - Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
B64D 35/02 - Transmitting power from power plant to propellers or rotors; Arrangements of transmissions characterised by the type of power plant
An oil recovery device for a reducer of an aircraft turbomachine, the device having a gutter extending around an axis and being intended to be arranged facing oil ejection means formed in a ring gear of the reducer of the turbomachine. The gutter can include at least one oil reception chamber which extends around the axis and which is open towards the axis so as to receive the oil coming from the oil ejection means. The reception chamber can be delimited by a first wall and a second wall arranged facing each other. The first wall can have an axial oil evacuation orifice and the second wall can have a radial dimension relative to the axis which increases increasingly along the axis towards the axial orifice, so as to allow oil ejected by the reducer to be conveyed to the axial orifice.
A power transmission system for an aircraft turbine engine including a speed reducer including a ring gear that is able to rotate about an axis X, formed from half-rings having annular flanges clamped together by first fastener. The reducer includes an annular channel for recovering centrifuged oil, having a U-shaped cross section, extending around the flanges, this channel being formed by an axial assembly of at least two parts and forming a fairing for the flanges and the first fastener intended to limit aerodynamic disturbances.
Lubrication module for at least one lubrication station of a turbomachine, the lubrication module comprising at least one positive displacement pump including a pump body delimiting a main chamber configured to be in fluid communication with a main lubrication circuit and an auxiliary chamber configured to be in fluid communication with an auxiliary lubrication circuit, and a piston movably mounted in the pump body between an inactive configuration and an active configuration, the piston being configured to perform, in the active configuration, a pumping movement between a top dead center and a bottom dead center by cooperation with a cam of a shaft of the turbomachine and, in the inactive configuration, not to cooperate with the cam of the shaft of the turbomachine, the positive displacement pump including a return element configured to return the piston to the active configuration.
The invention relates to a gear train comprising a sun gear (10) having a central axis (X), a ring gear (20) arranged coaxially around the sun gear (10), a planet carrier (30), and a first and a second plurality of planet gears (31, 32). Each planet gear (31, 32) is supported by the planet carrier (30) and comprises at least one first toothset (34a, 34b) meshing with the ring gear (20) and two second toothsets (35a-35d) meshing with the sun gear (10) and offset with respect to each other in the axial direction. Each of the first toothsets (34a, 34b) of the first and second plurality of planet gears (31) has a first median diameter (D1), and each of the second toothsets (35a-35d) of the first and second plurality of planet gears (32) has a second median diameter (D2) greater than the first median diameter (D1). The second toothsets (35c, 35d) of the second plurality of planet gears (32) are arranged, in said axial direction, between the second toothsets (35a, 35b) of the first plurality of planet gears (31).
The invention relates to a gear train comprising a sun gear (10) having a central axis (X), a ring gear (20) arranged coaxially around the sun gear (10), a planet carrier (30), and a first and a second plurality of planet gears (31, 32). Each planet gear (31, 32) is supported by the planet carrier (30) and comprises two first toothsets (34a, 34b) meshing with the ring gear (20) and offset with respect to each other in an axial direction parallel to the central axis (X). Each planet gear (31) of the first plurality of planet gears (31) comprises two second toothsets (35a, 35b) meshing with the sun gear (10) and offset with respect to each other in said axial direction. Each planet gear (32) of the second plurality of planet gears (32) comprises one or two second toothsets (35c, 35d) meshing with the sun gear (10). Each of the first toothsets (34a, 34b) of the first and second plurality of planet gears (31) has a first median diameter (D1), and each of the second toothsets (35a-35d) of the first and second plurality of planet gears (32) has a second median diameter (D2) greater than the first median diameter (D1). Each second toothset (35c, 35d) of the second plurality of planet gears (32) is arranged, in said axial direction, between the second toothsets (35a, 35b) of the first plurality of planet gears (31).
A planet carrier for a mechanical gearbox of a turbomachine, in particular for an aircraft, the planet carrier being formed in a single piece and comprising two annular flasks connected by material bridges and together defining housings configured to receive planet gears, the flasks comprising orifices for mounting the planet gears which are oriented axially and which open into the housings. One of the flasks can include at least one thinning around its orifices, the at least one thinning defining a minimum thickness of material in the axial direction which is less than a minimum thickness of the other flask around each of its orifices.
A propulsion system includes a drive shaft that rotates about an axis, a fan, a fan shaft that drives the fan about the axis, a reduction mechanism coupling the drive and fan shafts, a compression section driven by the drive shaft, and an inlet channel that extends between the fan and the compression section. The inlet channel includes inner and outer ferrules delimiting an air inlet flow path, the inner ferrule having a minimum radius. The reduction mechanism includes two reduction stages including two or more planet gears circumferentially distributed around the axis, each planet gear including a first portion meshed with the drive shaft and a second portion meshed with the fan shaft and being mounted fixed with respect to the inner ferrule and having a maximum radius greater than the minimum radius such that the air inlet flow path extends partly between the two or more planet gears.
F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user
F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan
F02C 7/04 - Air intakes for gas-turbine plants or jet-propulsion plants
A pre-assembly method for an aircraft turbomachine, having preliminary assembling, outside the turbomachine, the following components with each other a reduction gear configured to transmit a rotation between at least two rotors of the turbomachine while modifying the speed and torque ratio from one to the other of said at least two rotors, a shaft kinematically coupled to the reduction gear and configured to be kinematically coupled to one of said at least two rotors, a bearing support, and at least one bearing mounted on the bearing support and configured to rotatably support the shaft.
A mechanical reducer for a turbomachine for an aircraft, this reducer having a sun gear with internal splines and an external toothing, a ring gear which extends around the sun gear and which has an internal toothing, planet gears which are arranged between the sun gear and the ring gear and which each have at least one external toothing meshing with the external toothing of the sun gear and the internal toothing of the ring gear, and a planet carrier which carries first bearings for guiding the planet gears in rotation. The reducer can further include at least one second bearing for guiding the sun gear in rotation. The at least one second bearing can be mounted between the sun gear and the planet carrier.
The invention relates to a lubricating oil deflector for a speed reduction gear of a turbomachine, the deflector comprising a body having a first end intended to be disposed facing a sun gear of the reduction gear, the first end being configured to receive oil from the sun gear and an opposite second end configured to discharge the oil from the body, the body including two side faces each intended to be disposed facing a planet gear of the reduction gear and each connecting the first and second ends together, the body including at least one inner oil guide channel that opens out at the first end and at the second end and is configured to discharge the oil by gravity through the second end.
A circular modular tray for the additive manufacturing of a part with an axis of revolution on a powder bed, characterised in that it consists of an assembly of modules that are concentrically coupled along a contiguous axis in a radial direction, the modules including an annular peripheral module and a circular central module.
B33Y 30/00 - ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING - Details thereof or accessories therefor
B33Y 40/20 - Post-treatment, e.g. curing, coating or polishing
A propulsion system includes a drive shaft movable in rotation about an axis of rotation, a low-pressure compressor driven in rotation by the drive shaft, the low-pressure compressor having a mean radius, a fan shaft, a fan driven in rotation by the fan shaft, a reduction mechanism coupling the drive shaft and the fan shaft, having a reduction ratio, and an inlet channel which extends between the fan and the low-pressure compressor, the inlet channel having an inlet adjacent to the fan and an outlet opposite the inlet and adjacent to the low-pressure compressor, the inlet having a mean radius. A first ratio between a ratio of a mean radius of the inlet channel and the mean radius of the low-pressure compressor, and the reduction ratio of the reduction mechanism, is strictly less than 0.35.
F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan
F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user
Speed reduction gear for an aircraft turbomachine. The reduction gear has a main axis and planet carrier having a cage and a cage carrier, a sun gear located in the cage and centred on the main axis, an annular row of planet gears arranged around the main axis and the sun gear and meshed with the sun gear, and a ring gear arranged around the axis and the cage and meshed with the planet gears. The cage and the cage carrier are connected to each other by connections whose bending flexibility is optimised.
The planet carrier (213) for a reduction gear (10) of a turbomachine (1), particularly an aircraft turbomachine, comprises: - a carrier frame (220) having at its periphery axial housings (280) distributed about said axis (X), - a carrier frame holder (222) comprising axial fingers (282) distributed about the axis (X) and engaged in said axial housings (280), and - connecting elements connecting said fingers (282) to walls of said housings (280), each of these connecting elements comprising a pivot (289) extending in a radial direction (A) relative to said axis (X), this pivot (289) being borne by one of the members and having an external surface (292) which in axial section has a convex shape and which collaborates with a cylindrical internal surface (285a) of an orifice (285) of the other of these members.
The invention relates to a plain bearing (11) for an aircraft turbomachine, said plain bearing (11) having a tubular body (10b) comprising: an outer cylindrical surface (20aa), an inner cavity (10c) designed to contain oil; - a primary lubrification groove (24) formed by a middle portion (20aa1) of the outer surface (20aa) and a main channel (10d) for supplying the primary groove (24) with oil, the plain bearing being characterised in that the outer surface (20aa) of the body (10b) further comprises at least one secondary lubrification groove (26) which is formed in an end portion (20aa2, 20aa3) of the outer surface (20aa) and is independent of the primary groove (24), and in that the body (10b) further comprises a secondary channel (27) for supplying the or each secondary groove (26) with oil.
A turbomachine includes a fan, a first casing with longitudinal axis X in which a motor shaft is rotated around the longitudinal axis X, a second casing surrounding and coaxial with the first casing, and a drive shaft connected to the motor shaft. The driveshaft is also connected to at least two electric machines via a power transmission angle gear device housed in a housing. The electric machines being intended are configured to take or inject power on the motor shaft. The housing has a coupling surface to which the two electric machines are coupled.
The invention relates to an oil manifold (18) for a mechanical reduction gear (11) of a turbine engine, which includes a body (19) comprising two opposing side surfaces (20) each configured to extend in part around a planet gear of said reduction gear (11), the body (19) further including an internal oil circulation cavity, characterised in that the manifold (18) comprises at least one tab (22) removably mounted on the body (19), said tab (22) extending from the body (19) as an extension of at least one side surface (20) and intended to be inserted at least in part into an annular groove (12b) of a sun gear (12) of the reduction gear (11).
A modular tray, for the additive manufacturing of a part with an axis of revolution on a powder bed, includes: a shaft-mounted circular module including a shaft provided with a circular tray at one of the ends thereof, the shaft and the circular tray being concentric; and a main support module including, in one face, a cavity configured for receiving the shaft-mounted circular module, the shaft being completely inserted in the cavity. The assembly of the shaft-mounted circular module and of the main support module define a planar top surface that is at least partly formed by the circular tray of the shaft-mounted circular module.
B22F 10/28 - Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM]
B22F 10/66 - Treatment of workpieces or articles after build-up by mechanical means
B22F 12/82 - Combination of additive manufacturing apparatus or devices with other processing apparatus or devices
B22F 10/64 - Treatment of workpieces or articles after build-up by thermal means
B33Y 30/00 - ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING - Details thereof or accessories therefor
B33Y 40/20 - Post-treatment, e.g. curing, coating or polishing
B29C 64/153 - Processes of additive manufacturing using only solid materials using layers of powder being selectively joined, e.g. by selective laser sintering or melting
ARRANGEMENT FOR AN AIRCRAFT TURBINE ENGINE HAVING IMPROVED LUBRICATION, THE ARRANGEMENT COMPRISING A SHAFT ROTATABLY COUPLED TO A FOLLOWING MEMBER BY MEANS OF SPLINES
An arrangement for an aircraft turbine engine, including a shaft and a follower element rotatably coupled to the shaft by a spline connection, the arrangement including upstream and downstream connections for radially centring the follower element relative to the shaft; means for spraying a lubricant into a collection cavity; a passage for receiving lubricant, which passage opens into the collection cavity and into a cavity for lubricating the splines which is partially defined by the upstream and downstream radial centring connections; and a passage for discharging lubricant, which passage opens into the cavity for lubricating the splines and outside the arrangement.
An aircraft turbine engine includes a turbine shaft having a first axis of rotation, a propulsion propeller having a second axis of rotation parallel to and spaced from the first axis, and a mechanical reduction gear coupled to the turbine shaft and rotating the propeller. The reduction gear has a sun gear connected to the turbine shaft, a ring gear, and at least two planet gears, each including a first external toothing that is meshed with an external toothing of the sun gear. A second external toothing is located within the ring gear and is meshed with an internal toothing of the ring gear.
Turbomachine (100) comprising a fan (120) arranged along a longitudinal axis (X) of the turbomachine, a primary duct (130) able to channel a primary air flow of the fan through a compressor, a combustion chamber and a turbine of the turbomachine, an annular nacelle surrounding the fan so as to delimit a secondary duct (140) able to channel a secondary air flow of the fan, the temperature of which secondary air flow is lower than that of the primary air flow of the fan, the secondary air flow of the fan extending around the primary air flow of the fan, and engine support arms (150) arranged around the longitudinal axis (X) between the annular nacelle and a hub which delimits the primary and secondary ducts. The turbomachine also comprises an electrical energy generation device (171, 172, 173, 174) mounted so as to be able to be arranged facing one of the support arms in the secondary air flow and being driven by the secondary air flow.
F01D 15/10 - Adaptations for driving, or combinations with, electric generators
F02C 7/04 - Air intakes for gas-turbine plants or jet-propulsion plants
F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan
B64D 41/00 - Power installations for auxiliary purposes
F03D 3/00 - Wind motors with rotation axis substantially perpendicular to the air flow entering the rotor
F03D 9/00 - Adaptations of wind motors for special use; Combinations of wind motors with apparatus driven thereby; Wind motors specially adapted for installation in particular locations
31.
Method for manufacturing a mechanical reducer for an aircraft turbomachine
A method for manufacturing a mechanical reducer for an aircraft turbomachine including a central pinion, an outer crown, N planet pinions, where N≥3, each planet pinion including a first stage meshing with the central pinion, and a second stage meshing with the outer crown, the method including the assembly marking, wherein N teeth of the central pinion are marked, and N pairs of teeth of the first stage of each planet pinion are marked, the N planet pinions each being marked identically, and the assembly of the mechanical reducer, so that the teeth of the pairs of marked teeth of the first stage of each planet pinion are disposed on either side of a marked tooth of the central pinion.
A power transmission module for an aircraft, the module including a torque input connected to a turbine shaft, a first torque output and a second torque output, the power transmission module including a mechanical reducer including a sun gear forming the torque input, and planet gears carried by a planet carrier, wherein each of the planet gears includes at least three independent toothings and further includes a first toothing meshed with the sun gear, a second toothing meshed with an element forming one of the torque outputs, and a third toothing meshed with another element.
A splined shaft includes splines evenly distributed over the periphery, wherein the splines being spaced apart from each other. At least one portion of the splines are spaced apart by a modified pitch p with respect to the nominal pitch pn of the splines. The ratio of the absolute value of the difference between the modified pitch and the nominal pitch, to the nominal pitch, i.e. |pn−p|/pn, is different from zero, for example between 0.5 and 5%.
A propulsion system includes a drive shaft, a fan, a fan shaft, and a reduction device coupling the drive and fan shafts. The reduction device includes a first reduction stage and a second reduction state, and include a sun gear, centered on an axis of rotation of the drive and fan shafts and driven in rotation by the drive shaft, a ring gear, coaxial with the sun gear and that drives the fan shaft in rotation about the axis, and planet gears distributed circumferentially about the axis between the sun and ring gears, each planet gear including a first portion which is meshed with the sun gear and a second portion which is meshed with the ring gear, a diameter of the first portion being different from a diameter of the second portion, and an oil transfer bearing positioned between the fan and the reduction device.
F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user
F02K 3/04 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type
36.
AERONAUTIC PROPULSION SYSTEM WITH IMPROVED PROPULSION EFFICIENCY
An aero-propulsion system includes a drive shaft, a low-pressure compressor, a fan shaft driving a fan, a reduction device that couples the drive shaft and the fan shaft, and an inlet channel which extends between the fan and the low-pressure compressor, the inlet having a predetermined mean radius, a ratio between a mean radius of the inlet channel and the mean radius of the low-pressure compressor, on the one hand, and the reduction ratio of the reduction mechanism, on the other hand, being less than 0.35.
F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan
F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user
37.
TURBOMACHINE HAVING A CONTRAROTATING TURBINE FOR AN AIRCRAFT
Turbomachine (10) having a contrarotating turbine for aircraft, the turbomachine comprising a contrarotating turbine (22) of which a first rotor (22a) is configured to rotate in a first direction of rotation and is connected to a first turbine shaft (36), and a second rotor (22b) is configured to rotate in an opposite direction of rotation and is connected to a second turbine shaft (38), the first rotor comprising turbine discs that are interleaved between turbine discs of the second rotor, said first shaft (36) being guided by at least two guide bearings (60, 62) mounted between this first shaft and a stator casing, and said second shaft (38) being guided by at least two guide bearings (56, 58) mounted between this second shaft and another stator casing (28).
F02C 3/067 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages having counter-rotating rotors
F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user
F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan
38.
Aeronautical propulsion system having a low leakage flow rate and improved propulsion efficiency
A propulsion system includes a drive shaft movable about an axis of rotation, a fan, a fan shaft that drives the fan, and a reduction device coupling the drive shaft and the fan shaft. The reduction device has first and second reduction stages and includes a sun gear, centered on the axis and driven by the drive shaft, a ring gear that is coaxial with the sun gear and that drives the fan shaft about the axis, and planet gears distributed circumferentially about the axis between the sun gear and the ring gear. Each planet gear includes a first portion meshed with the sun gear and a second portion meshed with the ring gear. A diameter of the first portion is different from a diameter of the second portion, and the first portion of the planet gears extend between the second portion of the planet gears and the fan.
a cage (220) comprising at its periphery housings (280) and second connection elements which are mounted in said housings and which cooperate with the first connection elements to form connections between the cage carrier (222) and the cage (220), which allow at least one degree of freedom,
b).
A planet carrier for a speed reduction gear of a turbomachine has a main axis X and includes a cage carrier with an annular row of axial fingers around the axis X, which carry first connecting elements. The carrier further includes a cage having at its periphery housings and second connecting elements that are mounted in the housings and that cooperate with the first connecting elements to form connections between the cage carrier and the cage, which allow at least one degree of freedom. The cage comprises two shells that are axially fastened to each other and separated from each other by a plane. The housings are formed respectively in the shells.
An assembly for a gas turbine engine includes a casing centered on a longitudinal axis and including an upstream portion, a central portion and a downstream portion arranged successively along the longitudinal axis, an attachment system include plural tie rods, and an accessory gearbox arranged within a space delimited axially by the upstream portion and the downstream portion and radially by the central portion, the accessory gearbox being solely attached to the upstream portion or solely attached to the downstream portion by the attachment system.
A mechanical part for an aircraft turbomachine, the mechanical part being made of metal and comprising at least one profiled surface configured to ensure an oil flow during operation. According to the invention, the surface includes a more hydrophobic and/or lipophobic coating than the surface or a surface texturing rendering the surface more hydrophobic and/or lipophobic
A mechanical part for an aircraft turbomachine is made of metal and includes at least one profiled surface configured to ensure an oil flow during operation. The surface has a hydrophobic and/or lipophobic coating or a surface texturing rendering the surface hydrophobic and/or lipophobic.
An impeller (230) for a planet carrier of a planetary gear speed reducer of a turbomachine, is configured intended to be rotatably secured to the planet carrier and to be rotated about an axis A of the speed reducer. The impeller has an annular shape about the axis and includes lubrication means (43, 45, 238), in particular for lubricating bearings of planet gears of the speed reducer. The lubrication means include an annular cavity (238) situated at the inner periphery of the impeller. The impeller includes an inner peripheral wall (246) closing the cavity (238) in the radial direction, and the impeller includes an annular port (248) that extends around the axis and that opens in the axial direction into the cavity in order to supply it with lubricating oil.
An oil restrictor for emergency lubrication of a component for an aircraft turbine engine includes a metal cylindrical body having a longitudinal axis and configured to be housed in and shrink-fitted into a cylindrical bore of a part of the turbine engine. The restrictor further includes an integrated oil circuit enabling oil to pass through the restrictor along the axial extent thereof. The body is a one-piece body, and the circuit has at least two oil channels recessed on an outer cylindrical surface of the body and extending around and/or along the axis.
F16N 29/02 - Special means in lubricating arrangements or systems providing for the indication or detection of undesired conditions; Use of devices responsive to conditions in lubricating arrangements or systems for influencing the supply of lubricant
F16H 57/04 - Features relating to lubrication or cooling
The invention relates to an epicyclic reduction gear for a turbomachine, including a sun wheel that is rotatable about a first axis (A); a ring gear surrounding the sun wheel and being rotatable about the first axis (A); at least one planetary gear that is rotatable about a second axis (B), the planetary gear being meshed with the sun wheel and the ring gear; an immobile planet carrier, the planetary gear being rotatably guided about the second axis (B) with respect to a bearing of the planet carrier; an item of equipment including a rotor. The invention is characterized in that the item of equipment is fastened to the bearing of the planet carrier and the rotor of the item of equipment is rotatably driven by the planetary gear.
Propulsion assembly (1, 1', 1'') for an aircraft, comprising at least two electric motors (20, 30) configured to be arranged in a wing (110) of the aircraft and each comprising a rotor having a motor shaft (22 , 32) which is movable around an engine axis (X), at least one propeller (10) supported by a propeller shaft (12) which is movable around a propeller axis (A) and mechanically coupled to the motor shaft (22, 32) of the at least two electric motors (20, 30), the propeller axis (A) being perpendicular to the motor axis (X) of the at least two electric motors (20, 30).
B64D 35/08 - Transmitting power from power plant to propellers or rotors; Arrangements of transmissions characterised by the transmission being driven by a plurality of power plants
B64D 35/04 - Transmitting power from power plant to propellers or rotors; Arrangements of transmissions characterised by the transmission driving a plurality of propellers or rotors
B64D 27/24 - Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
An epicyclic reduction gear for a turbomachine includes a sun gear that is rotatable about a first axis and a ring gear surrounding the sun gear and also rotatable about the first axis. The ring gear is secured to a ring gear carrier that rotates a fan shaft. At least one planet gear is rotatable about a second axis and is meshed with the sun gear and the ring gear. The planet gear is guided in rotation about the second axis relative to a bearing of the planet carrier. A piece of equipment comprising a rotor. The piece of equipment is attached to the bearing of the planet carrier and has a rotor rotated by the ring gear carrier.
F16H 57/08 - General details of gearing of gearings with members having orbital motion
F16H 1/28 - Toothed gearings for conveying rotary motion with gears having orbital motion
F16H 57/021 - Shaft support structures, e.g. partition walls, bearing eyes, casing walls or covers with bearings
F16H 61/66 - Control functions within change-speed- or reversing-gearings for conveying rotary motion specially adapted for continuously variable gearings
49.
TURBINE ENGINE FOR AN AIRCRAFT COMPRISING ELECTRIC MACHINES
The invention relates to a turbine engine (1, 1') for an aircraft, comprising a gas turbine (2), a first electric machine (7a) comprising a first power transmission shaft (8a) having an axis of rotation (B ) extending substantially radially relative to the longitudinal axis (A), a second electric machine (7b) comprising a second power transmission shaft (8b) having an axis of rotation (B') extending substantially radially relative to the longitudinal axis (A), at least one mechanical transmission module (10) connecting the first and second electric machines (7a, 7b) to the gas turbine (2), the mechanical transmission module (10) comprising: an intermediate shaft (11) connected to the turbine shaft (3) and having a first bevel gear (12a) mounted thereon, a first input gear (13a) mounted on one end of the first transmission shaft (8a) and engaging with the first bevel gear (12a), and a second input gear (13b) mounted on one end of the second transmission shaft (8b) and engaging with the first bevel gear (12a).
planet gears which are meshed with the sun gear and the crown and which are held by a planet carrier (62) which is configured to be movable in rotation about said axis (61), In addition, the oil distributor (65) comprises a plurality of oil distribution modules (67) assembled together, each module (67) comprising at least one lubrication pipe (68) having an inlet intended to receive oil and an outlet (69) adapted to lead the oil into an opening (63) of the planet carrier (62), the opening (63) being intended for lubricating the reducer.
A triple-flow turbomachine for an aircraft, including a power transmission module including a torque input connected to a turbine shaft, a first torque output of a gearbox connected to a main shaft for rotatably driving a main fan propeller, and a second torque output of a planet gear connected to a secondary shaft for rotatably driving a secondary fan propeller. The planet gear is independent of the gearbox and arranged downstream of the gearbox.
F02K 3/077 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type the plant being of the multiple flow type, i.e. having three or more flows
52.
Planet carrier for a mechanical gearbox of an aircraft turbomachine
A planet carrier for a mechanical gearbox for a turbomachine includes a one-piece cage that extends about an axis of rotation defining an internal housing configured to receive a sun gear and planet gears of the gearbox. The planet carrier further includes a lubrication system with at least one bore formed in the cage and extending parallel to the axis over more than 30% of a maximum axial dimension (Lmax) of the cage. The lubrication system also includes for the at least one bore, at least two sprinklers which are fitted to the cage and which are each mounted in a recess of the cage.
The invention relates to a power transmission system for an aircraft turbine engine comprising a speed reducer (32) comprising a ring gear (40) that is able to rotate about an axis X, formed from half-rings (40a, 40b) having annular flanges (42a, 42b) clamped together by first fastening means (60), the reducer comprising an annular channel (62) for recovering centrifuged oil, having a U-shaped cross section, extending around the flanges (42a, 42b), this channel being formed by an axial assembly of at least two parts (74a, 74b) and forming a fairing for the flanges and the first fastening means (68) intended to limit aerodynamic disturbances.
F02C 3/107 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with two or more rotors connected by power transmission
F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user
F16H 57/04 - Features relating to lubrication or cooling
54.
Oil collector for a torque transmission device of an aircraft turbine engine
An oil collector for a torque transmission device of an aircraft turbine engine, this oil collector being configured to collect sprayed oil, wherein it includes at least one wall formed at least in part by a mesh structure, and at least one recovery device located at one end of the wall and configured to recover the oil captured by the wall and intended to flow from this wall to the recovery device.
A mechanical gearbox for turbomachine, in particular for aircraft. The gearbox includes a sun gear including an external toothing, a ring gear including an internal toothing, and planet gears which are meshed with the sun gear and the stationary ring gear. The planet gears are carried by a movable planet carrier and each having external toothings of different diameters. The movable planet carrier includes a movable ring gear which carries an internal toothing and which is independent of the stationary ring gear, each of the planet gears being meshed with the sun gear and the stationary and movable ring gears.
A mechanical reduction gear for a turbomachine, in particular for an aircraft, the reduction gear including a sun gear, a ring gear, planet gears which are meshed with the sun gear and the ring gear, hydrodynamic bearings for guiding the planet gears in rotation, these bearings being carried by a planet carrier and including cylindrical bodies which are engaged in the planet gears and which are configured so as to be supplied with oil and so as to form guiding oil films between the bodies and the planet gears, wherein each of the planet gears is guided by two hydrodynamic bearings independent of each other and disposed on either side of the plane.
The present invention relates to an aeronautical propulsion system (1) comprising a reduction mechanism (12) that couples a drive shaft (10) and a fan shaft (13), and an inlet channel (3) comprising an inner shroud (16) having a predetermined minimum radius (R2). The reduction mechanism (12) comprises two reduction stages (27, 32) comprising satellites (28), each having a first portion (38) that meshes with the drive shaft (10) and a second portion (39) that meshes with the fan shaft (13), each satellite (28) being mounted so as to be stationary relative to the inner shroud (16) of the inlet casing (3) and having a predetermined maximum radius (R1) which is greater than the minimum radius (R2) of the inner shroud (16) of the inlet channel (3) such that the air inlet duct extends at least partially between the two satellites (28).
F02C 7/04 - Air intakes for gas-turbine plants or jet-propulsion plants
F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user
F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan
58.
Mechanical reduction gear for an aircraft turbine engine
A mechanical reduction gear of a turbine engine, in particular for an aircraft, includes a sun gear having external toothing, a ring gear which extends around the sun gear and has internal toothing, planet gears which are in mesh with the sun gear and the ring gear and which have toothings of different diameters, a planet carrier which supports bearings for guiding the planet gears in rotation, and a lubrication circuit of the reduction gear. The planet carrier has a hydrodynamic abutment on which the sun gear is configured to bear axially.
A reduction gear for a turbomachine (6) extending around an axis (X-X) of rotation, comprising a ring gear (9) connected to a ring gear carrier (12), wherein the ring gear carrier (12) has, according to a section view along a plane including the axis (X-X), an internal segment (124), an external segment (126) and a ring gear support (128), extending successively from the internal shaft (122) until the ring gear support (128), the internal segment (124) extends until a radius R1 with respect to the axis (X-X), the external segment (126) forms an angle β with the internal segment (124), the ring gear support (128) forms an angle α with the external segment (126), and is secured to the ring gear (9) via a bolted connection accomplished at a nominal radius R2 with respect to the axis (X-X), in that the ratio R1/R2 is comprised between 0.3 and 0.7.
planet gears which are meshed with the sun gear and the ring gear and which each have a first toothing of average diameter D32 meshed with the toothing of the sun gear, and a second toothing of average diameter D28, different from D32, meshed with the internal toothing of the ring gear. The planet gears are guided by hydrodynamic bearings which each include a first smooth guiding surface extending at least partly under the first toothing, and a second smooth guiding surface extending at least partly under the second toothing.
F16C 32/06 - Bearings not otherwise provided for with moving member supported by a fluid cushion formed, at least to a large extent, otherwise than by movement of the shaft, e.g. hydrostatic air-cushion bearings
F16H 57/08 - General details of gearing of gearings with members having orbital motion
B64D 35/02 - Transmitting power from power plant to propellers or rotors; Arrangements of transmissions characterised by the type of power plant
The invention relates to a circular modular tray for the additive manufacturing of a part with an axis of revolution on a powder bed, characterised in that it consists of an assembly of modules that are concentrically coupled along a contiguous axis in a radial direction, the modules comprising an annular peripheral module (3) and a circular central module (2).
B29C 64/153 - Processes of additive manufacturing using only solid materials using layers of powder being selectively joined, e.g. by selective laser sintering or melting
The invention relates to a circular modular tray for the additive manufacturing of a part with an axis of revolution on a powder bed, characterised in that it consists of an assembly of modules that are concentrically coupled along a contiguous axis in a radial direction, the modules comprising an annular peripheral module (3) and a circular central module (2).
B29C 64/153 - Processes of additive manufacturing using only solid materials using layers of powder being selectively joined, e.g. by selective laser sintering or melting
B22F 10/28 - Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM]
B22F 10/37 - Process control of powder bed aspects, e.g. density
B22F 10/47 - Structures for supporting workpieces or articles during manufacture and removed afterwards characterised by structural features
B22F 10/60 - Treatment of workpieces or articles after build-up
B33Y 30/00 - ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING - Details thereof or accessories therefor
B33Y 40/20 - Post-treatment, e.g. curing, coating or polishing
A mechanical gearbox for an aircraft turbomachine includes a sun gear having an axis (X) of rotation, a ring gear around the sun gear, and planet gears meshed with the sun gear and the ring gear. Each planet gear has a first toothing meshed with the sun gear and a second loathing meshed with the ring gear. The first toothing includes a series of upstream teeth and a series of downstream teeth located on either side of a plane (H) perpendicular to the axis (X) of rotation of the sun gear. The second toothing includes a series of upstream teeth and a series of downstream teeth located on either side of the plane (H) and separated from one another by the first toothing, these teeth being parallel to one another and to the axis (Y) of rotation of the planet gear.
F16H 1/28 - Toothed gearings for conveying rotary motion with gears having orbital motion
F16H 57/08 - General details of gearing of gearings with members having orbital motion
F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user
F16H 1/34 - Toothed gearings for conveying rotary motion with gears having orbital motion involving gears essentially having intermeshing elements other than involute or cycloidal teeth
64.
Mechanical reduction gear for aircraft turbomachine
A mechanical reduction gear for turbomachine, in particular for aircraft. The reduction gear includes a sun gear having an axis of rotation, a ring gear which extends around the sun gear, planet gears which are meshed with the sun gear and the ring gear and which each includes a first toothing and a second toothing each including two series of teeth located on either side of a median plane, each of the planet gears being centred and guided in rotation by bearings, including an upstream bearing interposed axially between the series of upstream teeth of the second toothing and the plane, and a downstream bearing interposed axially between the series of downstream teeth of the second toothing and the plane.
The invention relates to a turbomachine comprising a fan, a first casing with longitudinal axis X in which a motor shaft is rotated around the longitudinal axis X, a second casing (23) surrounding and coaxial with the first casing, and a drive shaft connected to the motor shaft. According to the invention, the driveshaft is also connected to at least two electric machines via a power transmission angle gear device housed in a housing (41), the electric machines being intended to take or inject power on the motor shaft, and in that the housing (41) comprises a coupling surface (42) to which the two electric machines are coupled.
The invention relates to a turbomachine comprising a fan (2), an engine shaft (14) caused to rotate about a longitudinal axis X in a first casing, a second casing surrounding and coaxial with the first casing, and a drive shaft (25) connected, on the one hand, to the engine shaft (14) and, on the other hand, to at least one first equipment item via a mechanical angle transmission device (40). According to the invention, the first equipment item (30) is a first electric machine, and the turbomachine (1) comprises a reduction gear (50) arranged kinematically between the first equipment item (30) and the first mechanical angle transmission device (40).
F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user
F16H 57/04 - Features relating to lubrication or cooling
68.
ARRANGEMENT FOR AN AIRCRAFT TURBINE ENGINE HAVING IMPROVED LUBRICATION, THE ARRANGEMENT COMPRISING A SHAFT ROTATABLY COUPLED TO A FOLLOWING MEMBER BY MEANS OF SPLINES
The invention relates to an arrangement (60) for an aircraft turbine engine, comprising a shaft (11) and a follower element (52) rotatably coupled to the shaft (11) by a spline connection (62), the arrangement comprising: - upstream and downstream connections (68a, 68b) for radially centring the follower element (52) relative to the shaft (11); - means (36) for spraying a lubricant into a collection cavity (74); - a passage (86) for receiving lubricant, which passage opens into the collection cavity (74) and into a cavity (66) for lubricating the splines which is partially defined by the upstream and downstream radial centring connections (68a, 68b); and - a passage (88) for discharging lubricant, which passage opens into the cavity (66) for lubricating the splines and outside the arrangement.
The invention relates to a modular tray (12) for the additive manufacturing of a part with an axis of revolution on a powder bed, characterised in that it comprises: - a circular shaft module (13) comprising a shaft provided with a circular tray at one end thereof, the shaft and the circular tray being concentric; and - a main support module (16) having a cavity (17) in one face configured to receive the circular shaft module (13), the shaft being inserted completely into the cavity; the assembly of the circular shaft module and the main support module defining a planar upper surface which is formed at least in part by the circular tray of the circular shaft module. A modular tray (12) for the additive manufacturing of a part with an axis of revolution on a powder bed, characterised in that it comprises: a circular shaft module (13) comprising a shaft provided with a circular tray at one end thereof, the shaft and the circular tray being concentric; and a main support module (16) having a cavity (17) in one face configured to receive the circular shaft module (13), the shaft being inserted completely into the cavity; the assembly of the circular shaft module and the main support module defining a planar upper surface which is formed at least in part by the circular tray of the circular shaft module.
B29C 64/153 - Processes of additive manufacturing using only solid materials using layers of powder being selectively joined, e.g. by selective laser sintering or melting
B33Y 30/00 - ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING - Details thereof or accessories therefor
B33Y 80/00 - Products made by additive manufacturing
B22F 3/105 - Sintering only by using electric current, laser radiation or plasma
70.
Mechanical reduction gear of an aircraft turbomachine
A mechanical reduction gear of a turbomachine, in particular of an aircraft. The reduction gear includes a sun gear, a ring gear surrounded by a ring gear carrier, and planet gears meshed with the sun gear and the ring gear. The ring gear carrier includes an axial abutment on which the ring gear is configured to bear, and helical external splines which are engaged in complementary internal splines of the ring gear carrier and which are configured to cooperate by sliding with the internal splines so as to force the ring gear to be held against the abutment in operation.
F16H 1/28 - Toothed gearings for conveying rotary motion with gears having orbital motion
F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user
F16H 57/08 - General details of gearing of gearings with members having orbital motion
F16H 1/32 - Toothed gearings for conveying rotary motion with gears having orbital motion in which the central axis of the gearing lies inside the periphery of an orbital gear
71.
Cage for a turbomachine speed reducer with planetary gear set
A planet-carrier cage is provided for a turbomachine speed reducer having a planetary gear set. The cage contains a central sun gear and an annular row of planet gears arranged around the sun gear axis and engaging both the sun gear and an internal gear that surrounds the cage. A periphery of the cage has axial receiving elements configured to receive axial fingers secured to a cage carrier of the speed reducer. Each receiving element is penetrated by a radial spindle that guides the rotation of a connection means, such as a swivel joint or a bearing, which is supported by the fingers. The spindles include means for projecting lubricating oil into regions in which the planet gears mesh with the internal gear.
An installation for mounting an outer sun gear in a reduction gear. The reduction gear includes an outer sun gear and planet gears meshing with an inner sun gear and with the outer sun gear and each mounted for free rotation around a pivot of a planet carrier. The outer sun gear includes a first crown having a first toothing and a second crown having a second toothing each meshing with first and second toothings of the planet gears. The installation includes a frame for supporting the reduction gear along its longitudinal axis, and first and second torque applicators, such as cylinders, that apply a torque around an axis of first and second rings, respectively. The first ring is configured to engage with the first crown of the outer sun gear and the second ring is configured to engage with a second crown of the outer sun gear.
Disclosed is a planet carrier (10) for a mechanical reduction gear (6) of a turbomachine (1), in particular for an aircraft, this planet carrier comprising a cage (14) formed as a single part with a shaft portion (15), the cage comprising two annular flanges (14a, 14b) that are connected together by bridges of material (16) that define, together and with the flanges, cavities (18) configured to receive planet gears (8), characterised in that it further comprises an annular groove (30) that is formed in the first flange into the bridges of material, this groove extending around the shaft portion and emerging axially on the side of this shaft portion.
A mechanical reduction gear for a turbomachine, in particular for an aircraft, including a first sun gear having a central axis forming a main axis of the reduction gear, a ring gear, planet gears, a planet carrier, and at least one electric generator, in which the electric generator has a first set of electromagnetic elements and a second set of electromagnetic elements, wherein one among the first and second set of electromagnetic elements is a first set of coils, each coil of this first set of coils being wound around a direction parallel to the main axis, and in which the other among the first and second set of electromagnetic elements is configured to induce a current in the first set of coils when it is driven with a relative movement with respect to the first set of coils.
F16H 1/28 - Toothed gearings for conveying rotary motion with gears having orbital motion
F01D 25/24 - Casings; Casing parts, e.g. diaphragms, casing fastenings
F01D 15/10 - Adaptations for driving, or combinations with, electric generators
B64D 41/00 - Power installations for auxiliary purposes
B64D 27/16 - Aircraft characterised by the type or position of power plant of jet type
H02K 7/116 - Structural association with clutches, brakes, gears, pulleys or mechanical starters with gears
H02K 7/18 - Structural association of electric generators with mechanical driving motors, e.g.with turbines
H02K 21/24 - Synchronous motors having permanent magnets; Synchronous generators having permanent magnets with stationary armatures and rotating magnets with magnets axially facing the armatures, e.g. hub-type cycle dynamos
The invention concerns an assembly comprising an epicycloidal gear train (10) having a central pinion (26), an outer crown (28) and satellite pinions (32) in engagement with the central pinion (26) and the outer crown (28) and each mounted freely rotatable on a satellite carrier (36), the central pinion (26) surrounding and being rotationally fixed to a shaft (24) and the gear train comprising means for lubricating the teeth and axes (34) of the satellite pinions (32), these means including an annular cup (56) fixed to the satellite carrier (36) opened radially inward. According to the invention, the assembly includes fixed oil spraying means (64) configured to spray oil towards oil deflecting means (70) towards the inside of the annular cup (56).
The present invention relates to an aeronautical propulsion system (1) comprising a reduction mechanism (12) that couples a drive shaft (10) and a fan shaft (13) comprising two reduction stages (27, 32) and including: - a sun gear (33), - an annulus (25), and - a series of planets (28) distributed circumferentially between the sun gear (33) and the annulus (25), each planet (28) comprising a first portion (38) meshing with the sun gear (33), and a second portion (39) meshing with the annulus (25), a diameter of the first portion (38) being different from a diameter of the second portion (39), the first portion (38) of the planets (28) extending between the second portion (39) of the planets (28) and the fan (2).
F02K 3/02 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan
F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user
77.
TURBOMACHINE HAVING A CONTRAROTATING TURBINE FOR AN AIRCRAFT
Turbomachine (10) having a contrarotating turbine for aircraft, the turbomachine comprising a contrarotating turbine (22) of which a first rotor (22a) is configured to rotate in a first direction of rotation and is connected to a first turbine shaft (36), and a second rotor (22b) is configured to rotate in an opposite direction of rotation and is connected to a second turbine shaft (38), the first rotor comprising turbine discs that are interleaved between turbine discs of the second rotor, said first shaft (36) being guided by at least two guide bearings (60, 62) mounted between this first shaft and a stator casing, and said second shaft (38) being guided by at least two guide bearings (56, 58) mounted between this second shaft and another stator casing (28).
F02C 3/067 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages having counter-rotating rotors
F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user
F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan
78.
AERO-PROPULSION SYSTEM WITH IMPROVED PROPULSION EFFICIENCY
The present invention relates to an aero-propulsion system (1) comprising: - a drive shaft (10), - a low-pressure compressor (4), - a fan shaft (13) driving a fan (2), - a reduction mechanism (12) coupling the drive shaft (10) and the fan shaft (13), and - an inlet channel (3) which extends between the fan (2) and the low-pressure compressor (4), the inlet (18) having a predetermined mean radius (R3), a ratio between a mean radius (R3) of the inlet channel (3) and the mean radius (R2) of the low-pressure compressor (4), on the one hand, and the reduction ratio of the reduction mechanism (12), on the other hand, being strictly less than 0.35.
F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user
F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan
The present invention relates to an aeronautical propulsion system (1) comprising: - a reduction mechanism (12) coupling a drive shaft (10) and a fan shaft (13) and comprising two reduction stages (27, 32) comprising: a sun gear (33), a ring gear (25), and a series of planet gears (28) circumferentially distributed between the sun gear (33) and the ring gear (25), each planet gear (28) comprising a first portion (38) forming the first reduction stage (27) meshed with the sun gear (33) and a second portion (39) forming the second reduction stage (32) meshed with the ring gear (25), a diameter of the first portion (38) being different from a diameter of the second portion (39), and - a rotating oil transfer (15) positioned between the fan and the reduction mechanism (12).
F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user
F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan
80.
Supply and recovery of lubricating oil in a mechanical reduction gear of an aircraft turbomachine
A lubricating oil distributor for a mechanical reduction gear of a turbomachine, in particular of an aircraft, includes a body of generally annular shape around an axis X and includes first and second independent oil circuits. The first oil circuit has a first oil inlet connected by a first chamber to several oil outlets distributed on the body around the axis X. The second oil circuit has a second oil inlet connected by a second chamber to several oil outlets distributed on the body around the axis X. The first and second chambers extend circumferentially around the axis X at different diameters, wherein the first and second oil circuits are formed in the body and are respectively a recovery circuit and an oil supply circuit for toothing of the reduction gear.
An oil supply device intended to supply oil to an epicyclic reduction gear, the oil coming from at least one oil injector fixed with respect to the reduction gear, the oil supply device including at least one cup which is integral with a planet carrier of the reduction gear and substantially annular open radially with respect to an axis of the reduction gear and the walls of which delimit a cavity supplied by the at least one oil injector and which supplies at least one of the oil distribution circuits of the reduction gear. The oil supply device is staged and includes at least two independent stages provided with cups coaxial, of different diameters, each supplying an associated oil circuit and configured to receive the oil axially, centripetally, or tangentially, or according to an inclined direction combining two of the directions.
An impeller for a planet carrier of a epicyclic speed reduction gear of a turbine engine is fixed in rotation to the planet carrier and is rotatable about an axis of the reduction gear. The impeller has an annular shape about the axis and includes means for lubricating in particular planet gear bearings of the reduction gear. The lubricating means include an annular cavity located at the inner periphery of the impeller, wherein the impeller has an inner peripheral wall that closes the cavity in the radial direction. The impeller further includes an annular aperture that extends around the axis and opens in the axial direction into the cavity to supply lubricating oil thereto.
Disclosed is an impeller (230) for a planet carrier of a planetary gear speed reducer of a turbomachine, the impeller (230) being intended to be rotatably secured to the planet carrier and to be rotated about an axis A of the speed reducer, the impeller having an annular shape about the axis and comprising lubrication means (43, 45, 238), in particular for lubricating bearings of planet gears of the speed reducer, the lubrication means comprising an annular cavity (238) situated at the inner periphery of the impeller, characterised in that the impeller comprises an inner peripheral wall (246) closing the cavity (238) in the radial direction, and in that the impeller comprises an annular port (248) that extends around the axis and that opens in the axial direction into the cavity in order to supply it with lubricating oil.
An impeller (130) for a planet carrier of a planetary gear speed reducer of a turbomachine, said impeller having a generally annular shape and comprising means (158) for supporting axes of rotation of planets of said reducer, said impeller comprising means for lubricating teeth of said planets and bearings of said axes, said lubrication means comprising an annular groove (138) located on the internal periphery of said impeller and opening radially towards the inside, said groove being connected to lubricant supply and/or spray means, characterised in that the impeller comprises dynamic annular sealing means (142, 144) located at the inner periphery of said impeller, on either side of the groove, and configured to interact with a stator (132) of the reducer or of the turbomachine intended to extend inside of and coaxially with the impeller.
Oil restrictor (30) for emergency lubrication of a component for an aircraft turbine engine, said restrictor comprising a metal cylindrical body having a longitudinal axis (A) and configured to be housed in and shrink-fitted into a cylindrical bore (24) of a part (10b) of the turbine engine, said restrictor comprising an integrated oil circuit (40) enabling oil to pass through the restrictor along the axial extent thereof, characterised in that the body is a one-piece body, and in that the circuit comprises at least two oil channels (42-46) recessed on an outer cylindrical surface (30a) of the body and extending around and/or along the axis.
F16N 29/02 - Special means in lubricating arrangements or systems providing for the indication or detection of undesired conditions; Use of devices responsive to conditions in lubricating arrangements or systems for influencing the supply of lubricant
F16H 57/04 - Features relating to lubrication or cooling
A lubricant nozzle for a planetary gear set speed reducer of a turbomachine, the nozzle having a generally elongate shape and including a body with a longitudinal axis B, the body having a longitudinal inner cavity in fluid communication with a lubricant inlet located at a longitudinal end of the body and with lubricant outlet apertures that are provided in an annular wall of the body and that extend substantially radially relative to axis B, wherein the apertures are formed in at least one boss of the body, which boss projects radially outwards on the wall and extends, about the axis, at an angular extent that does not exceed 180°.
An oil collector for a mechanical reduction gear of a turbomachine, in particular for an aircraft, the reduction gear including a body having two opposite lateral faces configured to extend in part around planet gears of the reduction gear, the collector further including an internal oil circulation cavity connected firstly to oil inlets located on the faces, and on the other hand to at least one oil outlet, characterised in that at least one of the faces comprises includes columns and rows of several inlets each having a recess with a progressively increasing cross-section, each recess being delimited by walls, at least some of the walls having a hydrodynamic profile.
A propulsion unit for an aircraft, including an engine and a propeller shaft and further a propeller with airfoils which is coupled to the propeller shaft and having electrical members consuming electrical power, sealing between a case and the propeller shaft being ensured by a dynamic seal housed between a rotating dynamic seal support secured to the propeller shaft and a dynamic seal support flange secured to an end portion of the case, the rotating dynamic seal support being secured to the propeller shaft and abutted against a bearing for supporting this propeller shaft, it is provided that the propulsion unit, in order to deliver electrical power to the electrical members, having a rotating transformer rotated by the propeller shaft and including a stator, a casing of which is secured to the dynamic seal support flange and a rotor, a casing of which is secured to this propeller shaft.
A planet carrier for an epicyclic speed reduction gear, comprising a torque transmission member of longitudinal axis A and an annular cage extending around the axis A and connected to a longitudinal end of the member, said cage comprising two flanks extending essentially radially with respect to the axis A and connected by bridges, seats extending axially between the flanks and being intended for supporting planet gears mounted rotatably about the seats, characterized in that said bridges comprise bars which cross one another essentially in the shape of an X, and of which the ends located on the side of said member are connected to said member by a ring extending around said axis A and comprising a continuous internal annular channel.
Disclosed is an epicyclic reduction gear (15) for a turbomachine comprising: - a sun gear (16) that is able to rotate about a first axis (A); - a ring gear (17) surrounding the sun gear (16) and able to rotate about the first axis (A), the ring gear (17) being secured to a ring gear carrier (18) capable of rotating a fan shaft; - at least one planet gear (19) that is able to rotate about a second axis (B), the planet gear (19); - a stationary planet carrier (20), the planet gear (19) being guided in rotation about the second axis (B) relative to a bearing (35) of the planet carrier (20); - a piece of equipment (22) comprising a rotor (23); characterised in that the piece of equipment (22) is attached to the bearing (35) of the planet carrier (20) and the rotor (23) of the piece of equipment (22) is rotated by the ring gear carrier (18).
The invention relates to an epicyclic reduction gear (15) for a turbomachine, comprising: - a sun wheel (16) that is rotatable about a first axis (A); - a ring gear (17) surrounding the sun wheel (16) and being rotatable about the first axis (A); - at least one planetary gear (18) that is rotatable about a second axis (B), the planetary gear (18) being meshed with the sun wheel (16) and the ring gear (17); - an immobile planet carrier (19), the planetary gear (18) being rotatably guided about the second axis (B) with respect to a bearing (29) of the planet carrier (19); - an item of equipment (21) comprising a rotor (22). The invention is characterized in that the item of equipment (21) is fastened to the bearing (29) of the planet carrier (19) and the rotor (22) of the item of equipment (21) is rotatably driven by the planetary gear (18).
A mechanical reduction gear is suitable for a turbomachine and, in particular, a turbomachine of an aircraft. The reduction gear includes a sun gear, a ring gear formed by two half-ring gears, planet gears arranged between the sun gear and the ring gear, and at least one shaft rotationally fixed to the ring gear. The reduction gear further includes an annular covering part that extends around the ring gear and is independently fixed by flanges and/or splines to each of the half-ring gears.
An oil pipe cover for a mechanical reduction gear of a turbomachine, for example of an aircraft, is configured to be fixed to a planet carrier of the reduction gear and to be mounted on an axial end of a hydrodynamic bearing tubular support of a planet gear of the reduction gear. The oil pipe cover has an annular body extending around an axis (Y) and having a mounting central orifice on the axial end. The body has two diametrically opposed circumferential deflectors: a first deflector having a circumferential oil guiding surface located radially outwards with respect to the axis (Y), and a second deflectors having a circumferential oil guiding surface located radially inwards with respect to the axis (Y).
A planetary gearset having a first planet gear, a second planet gear, and pinion gears. The pinion gears mesh with the first planet gear and with the second planet gear, and each pinion gear is pivotally mounted around a shaft. A pinion gear carrier supports each shaft. Each shaft has a radially inner cylindrical portion mounted on the pinion gear carrier, a radially outer cylindrical portion about which the pinion gear is pivotally mounted and a flange extending radially from the radially outer cylindrical portion. The radially outer periphery of the flange is mounted on the pinion gear carrier. The radially outer cylindrical portion and the radially inner cylindrical portion are connected to each other by a radially extending connecting zone.
A speed-reducing unit, particularly for transferring torque between a gas turbine and a fan in a turbine engine, includes an annular ring, at least one gear that is coupled to the ring, the ring including two annular half-rings that are offset relative to each other along the main axis of the speed-reducing unit and that are coupled with at least one gear, and a plate for supporting the two half-rings, in relation to which the two half-rings are rotationally fixed about the main axis of the speed-reducing unit. Each half-ring includes an internal helical tooth. Each half-ring is connected to the support plate so as to be able to be uncoupled from at least one gear when at least one gear exerts a disengaging action on each half-ring, with the amplitude of the action being greater than a determined amplitude value.
The invention relates to a planet-carrier (230) cage (234) for a turbomachine speed reducer (110) with a planetary gear set, said cage being designed such that it can contain a central sun wheel (151) with an axis of rotation X and an annular row of planets (150) arranged around the axis X and engaged with said sun wheel, the cage comprising axial receiving elements (280) on the periphery thereof, for receiving axial arms (282) secured to a barrel (242) of said reducer, a substantially radial finger (288) passing through each receiving element and being used to guide the rotation of a ball joint (286) carried by one of said arms, characterised in that each finger comprises means (294, 295) for lubricating said ball joint.
A mechanical reduction gear for a turbomachine, in particular for an aircraft, this reduction gear including a sun gear having an axis of rotation, a ring gear which extends around the sun gear and which is configured to be fixed in rotation around the axis, planet gears which are in mesh with the sun gear and the ring gear and which are held by a planet carrier which is configured to be fixed or in rotation around the axis, each planet gear including a first toothing of average diameter D1 for the meshing with the sun gear, and a second toothing of average diameter D2, different from D1, for the meshing with the ring gear, wherein the first and second toothings of each planet gear include herringbone teeth and are symmetrical with respect to a plane perpendicular to the axis and passing substantially in the middle of the planet gear.
A mechanical reduction gear for a turbomachine, in particular for an aircraft, this reduction gear including a sun gear having an axis of rotation, a ring gear that extends around the sun gear, planet gears which are meshed with the sun gear and the ring gear, and a lubricating oil distributor which is configured to supply oil to the internal cavities of tubular supports of the planet gears, wherein each of the tubular supports includes a first angular sector including oil conveying pipes and a first outer peripheral surface for forming an oil film, and a second angular sector including a second outer peripheral surface in which a breaking tub of the oil film and recovering of the oil is formed.
The invention relates to the lubrication of a planet-carrier for a mechanical reduction gear of a turbine engine, in particular of an aircraft, said planet-carrier comprising a cage defining an internal housing intended to receive a central sun gear with an axis of rotation X, and an annular row of planet gears arranged around the sun gear, said cage comprising two annular walls that are radial with respect to said axis X, and connected to one another at their outer periphery by a cylindrical wall of axis X, at least one of these radial walls comprising orifices for mounting the axes of said planet gears, and the cylindrical wall comprising through-holes for the passage of the gearings of the planet gears so that they may engage with a gearing of the ring gear, which is intended to extend around the planet gears and the cage.
