Patents by Inventor Alain Dominique Gendraud
Alain Dominique Gendraud has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Publication number: 20230212953Abstract: The invention proposes an aeronautical turbine engine assembly comprising an upstream casing (55) to which guide blading (48a) is fastened, and a downstream casing (58) to which a sealing element (62) provided with an abradable material for rotor blading is fastened. This assembly further comprises a shroud ring (66) placed between the upstream casing and the downstream casing and fastening means (68) for detachably fastening the shroud ring. In order to be fastened to the upstream casing, the guide blading (48a) of the turbine engine is mounted on a downstream hook (480b) of the upstream casing, without being hooked onto the shroud ring (66), and the downstream casing (58) has an upstream hook with which the sealing element (62) is engaged in order to be fastened to the downstream casing, or the shroud ring has an upstream hook on which the sealing element (62) is mounted so as to be fastened to the downstream casing.Type: ApplicationFiled: April 28, 2021Publication date: July 6, 2023Inventors: Simon Nicolas MORLIERE, Nicolas Jean-Marc Marcel BEAUQUIN, Thierry FACHAT, Alain Dominique GENDRAUD
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Patent number: 11585237Abstract: A system for the axial retention of a holding ring for a bearing for guiding in rotation a rotary shaft of a turbomachine is disclosed. The system includes an annular bearing support and a bearing holding ring that is borne by the annular bearing support. The bearing holder ring includes an upstream ring configured to be brought into contact with the bearing support and a downstream ring that is elastically deformable. The bearing support has a first axial retention element, and the bearing holding ring has a second axial retention element. The first and second axial retention elements are configured to cooperate with one another to axially retain the bearing holding ring in the event of damage to the downstream ring.Type: GrantFiled: September 3, 2019Date of Patent: February 21, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Christophe Lima, Boucif Bensalah, Alain Dominique Gendraud, Alberto Martin Matos, Valentin Olivier Jean-Jacques Quesnel
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Publication number: 20220290579Abstract: The invention relates to an assembly (25) for a turbomachine turbine comprising a casing (18) including an annular wall (26) extending about an axis, and means of cooling the casing (18), the said means of cooling comprising a collector housing (22) and at least one tube (23) extending circumferentially around the annular wall (26) of the casing (18) and connected to the housing (22), with the tube (23) comprising cooling-air ejection orifices.Type: ApplicationFiled: August 4, 2020Publication date: September 15, 2022Inventors: Simon Nicolas MORLIERE, Stéphane Pierre Guillaume BLANCHARD, Nicolas Jean-Marc Marcel BEAUQUIN, Alain Dominique GENDRAUD, Olivier RENON
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Patent number: 11441431Abstract: The present disclosure relates to a holding system for the dismantling of a blade wheel, the blade wheel comprising: a disc, a plurality of blades configured to be mounted circumferentially around the disc, the plurality of blades defining a plurality of inter-blade spaces, each of the inter-blade spaces being defined circumferentially between two adjacent blades of the plurality of blades, the holding system comprising a plurality of inserts, each of the inserts being configured to be inserted into each of the inter-blade spaces in a holding position so as to hold the relative position of the blades when the plurality of blades is dismantled from the disc.Type: GrantFiled: June 6, 2019Date of Patent: September 13, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Nicolas Daniel Delaporte, Alain Dominique Gendraud, Emmanuel Bernard Marie Charrier
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Publication number: 20220034237Abstract: A system for the axial retention of a holding ring for a bearing for guiding in rotation a rotary shaft of a turbomachine is disclosed. The system includes an annular bearing support and a bearing holding ring that is borne by the annular bearing support. The bearing holder ring includes an upstream ring configured to be brought into contact with the bearing support and a downstream ring that is elastically deformable. The bearing support has a first axial retention element, and the bearing holding ring has a second axial retention element. The first and second axial retention elements are configured to cooperate with one another to axially retain the bearing holding ring in the event of damage to the downstream ring.Type: ApplicationFiled: September 3, 2019Publication date: February 3, 2022Applicant: SAFRAN AIRCRAFT ENGINESInventors: Christophe Lima, Boucif Bensalah, Alain Dominique Gendraud, Alberto Martin Matos, Valentin Olivier Jean-Jacques Quesnel
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Publication number: 20210254481Abstract: The present disclosure relates to a holding system for the dismantling of a blade wheel, the blade wheel comprising: a disc, a plurality of blades configured to be mounted circumferentially around the disc, the plurality of blades defining a plurality of inter-blade spaces, each of the inter-blade spaces being defined circumferentially between two adjacent blades of the plurality of blades, the holding system comprising a plurality of inserts, each of the inserts being configured to be inserted into each of the inter-blade spaces in a holding position so as to hold the relative position of the blades when the plurality of blades is dismantled from the disc.Type: ApplicationFiled: June 6, 2019Publication date: August 19, 2021Applicant: SAFRAN AIRCRAFT ENGINESInventors: Nicolas Daniel DELAPORTE, Alain Dominique GENDRAUD, Emmanuel Bernard Marie CHARRIER
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Patent number: 10920593Abstract: A movable ring assembly (4) for a turbine engine turbine (10) that is mounted between two successive rotor discs (20a) and (20b) of said turbine (10), said rotor discs (20a) and (20b) being fixed to each other by bolting, characterised in that it comprises:—a fixing ferrule (44) fixed between the upstream (20a) and downstream (20b) discs by the bolting thereof; a part forming a movable ring (42), said part supporting radial sealing members (32) and being fixed between the upstream disc (20a) and the ferrule (44);—and a seal (46) interposed between said part forming the movable ring (42) and the ferrule (44).Type: GrantFiled: October 6, 2017Date of Patent: February 16, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Vincent Francois Georges Millier, Francois Pierre Michel Comte, Fabien Stephane Garnier, Alain Dominique Gendraud, Arnaud Lasantha Genilier
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Patent number: 10900382Abstract: An assembly includes a securing stud held by a locking key that rotates with the stud and is provided with bearing surfaces for sitting on an edge of one of the parts to be assembled.Type: GrantFiled: July 19, 2016Date of Patent: January 26, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Alain Dominique Gendraud, Jean-Baptiste Vincent Desforges, Arnaud Genilier, Reda Oudyi
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Publication number: 20200040735Abstract: A movable ring assembly (4) for a turbine engine turbine (10) that is mounted between two successive rotor discs (20a) and (20b) of said turbine (10), said rotor discs (20a) and (20b) being fixed to each other by bolting, characterised in that it comprises:—a fixing ferrule (44) fixed between the upstream (20a) and downstream (20b) discs by the bolting thereof; a part forming a movable ring (42), said part supporting radial sealing members (32) and being fixed between the upstream disc (20a) and the ferrule (44);—and a seal (46) interposed between said part forming the movable ring (42) and the ferrule (44).Type: ApplicationFiled: October 6, 2017Publication date: February 6, 2020Applicant: SAFRAN AIRCRAFT ENGINESInventors: Vincent Francois Georges MILLIER, Francois Pierre Michel COMTE, Fabien Stephane GARNIER, Alain Dominique GENDRAUD, Arnaud Lasantha GENILIER
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Patent number: 10344610Abstract: A turbomachine module, comprising a mobile wheel rotatably mounted inside a housing of the module and surrounded by a sectorised sealing ring (18) that comprises an annular row of sectors, each ring sector comprising at least one circumferential hook that is configured to engage with an annular hooking rail of the housing, the module further comprising a sectorised protective annular shim (50) that is interposed between the hooks of the ring sectors and the rail of the housing and that comprises an annular row of sectors of shim, characterised in that the edges (60) of the circumferential ends of the sectors of shim are not aligned with the edges (58) of the circumferential ends of the ring sectors along the longitudinal axis of the module.Type: GrantFiled: August 4, 2015Date of Patent: July 9, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Cyril Loiseau, Alain Dominique Gendraud, Sebastien Jean Laurent Prestel
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Publication number: 20180209302Abstract: An assembly including a securing stud held by a locking key that rotates with the stud and is provided with bearing surfaces for sitting on an edge of one of the parts to be assembled. Sufficient clamping torque can be introduced without risk of damage and at the same time avoiding excessive screwing of the stud.Type: ApplicationFiled: July 19, 2016Publication date: July 26, 2018Applicant: SAFRAN AIRCRAFT ENGINESInventors: Alain Dominique GENDRAUD, Jean-Baptiste Vincent DESFORGES, Arnaud GENILIER, Reda OUDYI
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Patent number: 9957841Abstract: A turbine stage for a turbine engine, the stage including a nozzle and a wheel mounted inside a sectorized ring carried by a casing. The nozzle is attached to the casing and is retained axially downstream by bearing against an annular split ring. Each ring sector includes at its upstream end a member of C-shaped section that is engaged on the casing rail and that holds the split ring radially. A radially inner wall of the C-shaped member of each ring sector extends inside the split ring over an entire axial dimension thereof and its upstream end portion is engaged in at least one recess of the nozzle.Type: GrantFiled: April 17, 2013Date of Patent: May 1, 2018Assignee: SNECMAInventors: Alain Dominique Gendraud, Alberto Martin-Matos, Vincent Millier, Sebastien Jean Laurent Prestel
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Patent number: 9726033Abstract: A rotor wheel for a turbine engine, such as an airplane turboprop or turbojet, the rotor wheel including a rotor disk including teeth at its outer periphery defining slots for axially mounting and radially retaining blade roots. An annular lip includes an annular rim extending axially downstream from and radially towards an inside of a radial retaining mechanism formed to project axially from an upstream face of the disk, and a sealing mechanism is arranged radially inside the annular lip and upstream ends of platforms of the blades.Type: GrantFiled: November 12, 2012Date of Patent: August 8, 2017Assignee: SNECMAInventors: Alain Dominique Gendraud, Fabrice Marcel Noel Garin, Romain Nicolas Lunel
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Publication number: 20170218785Abstract: A turbomachine module, comprising a mobile wheel rotatably mounted inside a housing of the module and surrounded by a sectorised sealing ring (18) that comprises an annular row of sectors, each ring sector comprising at least one circumferential hook that is configured to engage with an annular hooking rail of the housing, the module further comprising a sectorised protective annular shim (50) that is interposed between the hooks of the ring sectors and the rail of the housing and that comprises an annular row of sectors of shim, characterised in that the edges (60) of the circumferential ends of the sectors of shim are not aligned with the edges (58) of the circumferential ends of the ring sectors along the longitudinal axis of the module.Type: ApplicationFiled: August 4, 2015Publication date: August 3, 2017Inventors: Cyril LOISEAU, Alain Dominique GENDRAUD, Sebastien Jean Laurent PRESTEL
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Patent number: 9683452Abstract: A turbine for a gas turbine engine comprising at least one turbine stator and one turbine rotor, said turbine stator comprising at least one inner annular platform, said inner platform comprising a radial wall delimiting at least one cavity between the turbine stator and the turbine rotor, wherein the turbine rotor comprises at least one elongate element positioned substantially axially and defining a sealing baffle in said cavity, and in that the turbine stator comprises at least one element made of abradable material designed to engage with said elongate element of the turbine rotor so as to form a labyrinth seal.Type: GrantFiled: December 19, 2013Date of Patent: June 20, 2017Assignee: SNECMAInventors: Florent Pierre Antoine Luneau, Alain Dominique Gendraud, Patrick Joseph Marie Girard, Sebastien Jean Laurent Prestel
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Patent number: 9631495Abstract: A turbomachine assembly in which a foil is configured to cover mainly one of bulbs of a disc and to be held, radially with respect to the disc, by the bulb of the disc and a pocket for a blade that can collaborate therewith, when these two are effectively collaborating, and the bulb of the disc includes at least one longitudinal cavity configured to form, with the foil, when the foil is covering the bulb of the disc, a secondary passage through which a secondary cooling air flow can pass.Type: GrantFiled: October 10, 2012Date of Patent: April 25, 2017Assignee: SNECMAInventors: Emmanuel Da Costa, Alain Dominique Gendraud, Renaud Martet, Josselin Sicard, Bruno Andre Jean Varin
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Patent number: 9103220Abstract: An interface element to be mounted between a blade root and a blade root housing provided in a turbine disc of a gas turbine engine to limit wear between the root and the housing. The interface element includes: a base, configured to be aligned with a lower part of the root; and first and second upper side walls connected to the base and configured to surround the blade root up to an upper portion thereof, the first upper side wall including at least one ventilation opening to allow a flow of cooling air flowing through the rotor disc housing to flow over the upper portion of the root via the ventilation opening.Type: GrantFiled: April 20, 2011Date of Patent: August 11, 2015Assignee: SNECMAInventors: Fabrice Marcel Noel Garin, Alain Dominique Gendraud, Thierry Lequitte, Romain Nicolas Lunel
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Patent number: 9080463Abstract: A turbine ring assembly includes a ring support structure and a plurality of ring sectors, each including a single piece of ceramic matrix composite material. Each ring sector includes a first portion forming an annular base with an inside face defining an inside face of the turbine ring and an outside face from which there extends two tab-forming portions including ends that are engaged in housings in the ring support structure. The ring sectors present a section that is substantially ?-shaped and the ends of the tabs are held without radial clearance by the ring support structure. The tabs can have a free length in meridian section that is not less than three times their mean width.Type: GrantFiled: March 1, 2010Date of Patent: July 14, 2015Assignees: SNECMA, HERAKLESInventors: Franck Roger Denis Denece, Alain Dominique Gendraud, Georges Habarou, Hubert Illand, Damien Bonneau
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Publication number: 20150118035Abstract: A turbine stage for a turbine engine, the stage including a nozzle and a wheel mounted inside a sectorized ring carried by a casing. The nozzle is attached to the casing and is retained axially downstream by bearing against an annular split ring. Each ring sector includes at its upstream end a member of C-shaped section that is engaged on the casing rail and that holds the split ring radially. A radially inner wall of the C-shaped member of each ring sector extends inside the split ring over an entire axial dimension thereof and its upstream end portion is engaged in at least one recess of the nozzle.Type: ApplicationFiled: April 17, 2013Publication date: April 30, 2015Applicant: SNECMAInventors: Alain Dominique Gendraud, Alberto Martin-Matos, Vincent Millier, Sebastien Jean Laurent Prestel
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Patent number: 8979489Abstract: The invention relates to a low pressure turbine (1) of a turbomachine comprising a nozzle (62) belonging to an upstream stage (20B) and a nozzle (162) belonging to a downstream stage (20C), the nozzle (62) forming segments (62a) having an external structure (66) comprising: a tab (76) bearing radially on a hook (79) fixed to the case, a tab (85) bearing radially on a reaming (87) in the case, the tabs (76, 85) delimiting an annular upstream cooling air circulation cavity (91), a contact surface (84) extending in the downstream direction from the tab (85) and lined with an abradable element (86) on the inside, the contact surface comprising a downstream end (92) bearing axially on the nozzle (162) and bearing radially on a stop (93) of the case, the contact surfaces (84) delimiting an annular downstream cooling air circulation cavity (94) communicating with cavity (91).Type: GrantFiled: November 21, 2011Date of Patent: March 17, 2015Assignee: SNECMAInventors: Jean-Claude Christian Taillant, Alain Dominique Gendraud