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公开(公告)号：US12055097B2
公开(公告)日：2024-08-06
申请号：US18549796
申请日：2022-03-08
发明人： Paul Ghislain Albert Levisse , Emmanuel Fabrice Marie Baret , Julien Fabien Patrick Becoulet , Alexandre Jean-Marie Tan-Kim
CPC分类号： F02C7/06 , F01D25/162 , F05D2240/50 , F05D2260/96
摘要： A device for centering and guiding a shaft of an aircraft turbine engine, the device including an outer ring of a rolling bearing, the ring extending about an axis; an annular bearing support extending about the axis and at least partially about the ring; at least one series of connecting elements for linking the ring to the support, the connecting elements being interposed between an inner cylindrical rim of the ring and an outer cylindrical rim of the support that extends about the inner rim, and each having a first radially outer end for linking to the outer cylindrical rim and a second radially inner end for linking to the inner cylindrical rim, the ring, the support and the connecting elements being integrally formed, the connecting elements being enclosed in an annular housing that is radially delimited by the rims and laterally enclosed by an annular web.
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公开(公告)号：US11773771B2
公开(公告)日：2023-10-03
申请号：US17782510
申请日：2020-12-07
发明人： Paul Ghislain Albert Levisse , Olivier Belmonte , Fabrice Joël Luc Chevillot , Clément Paul René Niepceron , Amélie Argie Antoinette Chassagne
CPC分类号： F02C3/067 , F02C7/06 , F02C7/36 , F05D2260/40311 , F05D2260/98
摘要： A turbomachine with a counter-rotating turbine for an aircraft includes a counter-rotating turbine and a mechanical reduction gear with an epicyclic, planetary-type gear train. The gear train includes a planet carrier secured to a stator housing of the turbomachine situated upstream from the counter-rotating turbine in relation to a direction of gas flow within the turbomachine. The planet carrier is secured to the stator housing by an annular part with an elongated shape extending inside the second shaft. The annular part includes an upstream end secured to the intermediate casing and a downstream end coupled to the planet carrier. The annular part also includes an integrated circuit for conveying lubrication oil from its upstream end to the planet carrier.
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3.发明授权公开(公告)号：US11708148B2
公开(公告)日：2023-07-25
申请号：US17996810
申请日：2021-04-13
摘要： The invention relates to a blade pivot with adjustable orientation for a turbomachine fan hub, comprising: a stud having a fastener configured to retain a blade root and coupling means for the transmission of a twist torque; a ball bearing for taking centrifugal forces having an inner ring and an outer ring; a first clamping nut intended to be screwed on an inner thread of the hub to ensure clamping of the outer ring of the ball bearing; a rolling-element bearing for taking transverse forces having an inner ring and a smooth outer ring; a locking ring mounted between these two inner rings to provide for them a respective transverse support; an anti-rupture sleeve carrying the inner ring of the rolling-element bearing for taking transverse forces and the terminal end of which is extended transversely beyond the outer ring of this bearing.
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公开(公告)号：US11988136B2
公开(公告)日：2024-05-21
申请号：US17756501
申请日：2020-12-08
发明人： Paul Ghislain Albert Levisse , Olivier Belmonte , Romain Truco , Olivier Formica , Fabrice Joel Luc Chevillot , Clement Paul Rene Niepceron
CPC分类号： F02C3/067 , F02C7/06 , F02C7/36 , F02K3/06 , F05D2220/323 , F05D2240/54 , F05D2260/40311
摘要： A turbomachine having a contrarotating turbine for an aircraft, the turbomachine including a contrarotating turbine of which a first rotor is configured to rotate in a first direction of rotation and is connected to a first turbine shaft, and a second rotor configured to rotate in an opposite direction of rotation and connected to a second turbine shaft. The first rotor includes turbine wheels interleaved between turbine wheels of the second rotor, the turbomachine further including a planetary-type epicyclic mechanical reduction gear which has a sun gear driven in rotation by the second shaft, a ring gear driven in rotation by the first shaft, and a planet carrier attached to a first stator casing of the turbomachine located upstream of the contrarotating turbine with respect to a direction of flow of gas in the turbomachine. The turbomachine includes bearings for guiding the first and second shafts.
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5.发明授权公开(公告)号：US11852079B2
公开(公告)日：2023-12-26
申请号：US17624113
申请日：2020-06-16
发明人： Emmanuel Fabrice Marie Baret , Julien Fabien Patrick Becoulet , Franck Emmanuel Bosco , Michel Gilbert Roland Brault , Paul Ghislain Albert Levisse
CPC分类号： F02C7/32 , F01D25/20 , F02C7/06 , F02C7/36 , F05D2220/323 , F05D2260/40 , F05D2260/98
摘要： A pump that can be a gear pump that drives a rotating body of an aircraft turbine engine such as a fan shaft, is set in rotation always in the same direction, by virtue of a transmission including an oblique double gear formed by a toothed wheel on the same side as the rotating body and meshing with two pinions connected to a shaft driving the pump through free-wheels with identical driving directions, whereas the pinions have opposite directions of rotation.
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公开(公告)号：US11643975B2
公开(公告)日：2023-05-09
申请号：US17603655
申请日：2020-04-17
发明人： Julien Fabien Patrick Becoulet , Emmanuel Fabrice Marie Baret , Franck Emmanuel Bosco , Michel Gilbert Roland Brault , Paul Ghislain Albert Levisse
CPC分类号： F02C7/36 , F01D25/18 , F02C7/06 , F16H57/0479 , F16H57/0486 , F16H57/082 , F05D2220/323 , F05D2240/60 , F05D2260/40311 , F05D2260/98
摘要： A speed reducer, particularly of an aircraft, includes a central sun gear mounted to rotate with a drive shaft about a rotation axis X, an annular ring gear coaxial with the X axis, and a plurality of planet gears arranged about the X axis and mounted to be movable on a planet carrier. The planet gears engages the sun gear and the annular ring gear, which extends around the planet gears. The speed reducer further includes a lubricant recovery device having a pipe for recovering lubricant discharged from the reducer by centrifuging. The recovery device has scoops mounted to pivot about a pivot axis P on a movable member of the speed reducer that rotates about the X axis between a deployed state and a rest state.
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公开(公告)号：US20230008678A1
公开(公告)日：2023-01-12
申请号：US17783629
申请日：2020-12-01
发明人： Paul Ghislain Albert Levisse , Olivier Belmonte , Fabien Roger Gaston Caty , Amelie Argie Antoinette Chassagne
摘要： Disclosed is a turbo machine (10) with counter-rotating turbine for an aircraft, comprising: - a high-pressure body, - a low-pressure counter-rotating turbine (22), - a planetary-type mechanical epicyclic reduction gear (42), - guide bearings (56-62) for the turbine shafts (36, 38), characterised in that said reduction gear (42) and certain of the bearings (60, 62) are housed in a lubrication chamber (86) supplied with oil and comprising dynamic seals (86a-86d), and in that the turbo machine comprises circuits (C1, C2) for pressurising these seals.
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公开(公告)号：US11994073B2
公开(公告)日：2024-05-28
申请号：US17906790
申请日：2021-03-25
CPC分类号： F02C7/36 , F01D15/12 , F01D25/16 , F02C3/06 , F02C3/107 , F02C7/06 , F02K3/06 , F16H1/28 , F05D2220/323 , F05D2240/50 , F05D2260/40
摘要： Aircraft turbomachine comprising a casing, a fan, a compressor and a turbine and an epicyclic gear train comprising an input driven in rotation by the turbine, a first output stage configured to drive in rotation the compressor and a second output stage coupled to the first output stage and configured to drive in rotation the fan, the compressor being driven in rotation by the ring gear of the first output stage.
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公开(公告)号：US11885265B2
公开(公告)日：2024-01-30
申请号：US17783634
申请日：2020-12-01
CPC分类号： F02C7/06 , F02C7/24 , F02C7/36 , F05D2260/40311 , F05D2260/602
摘要： Aircraft turbine engine (10), comprising:—at least one first turbine rotor (22a) connected to a first turbine shaft (36) and comprising rotor blades located in a stream (V),—an annular exhaust casing (28) supporting at least one bearing (60, 62) for guiding the rotation of the first shaft and comprising arms (28a) located in the stream, downstream of the blades, and—a mechanical planetary gearbox (42) which comprises a sun gear (44), a ring gear (40) and a planet carrier (46), the gearbox being at least partially surrounded by the exhaust casing and one of the rotatable elements chosen from the sun gear and the ring gear being connected to the first shaft, characterised in that the exhaust casing carries a device (70) for recovering and discharging oil projected centrifugally by the reduction gear.
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公开(公告)号：US11754342B2
公开(公告)日：2023-09-12
申请号：US17604233
申请日：2020-04-14
发明人： Paul Ghislain Albert Levisse , Pierre Jean-Baptiste Metge , Alexandre Corsaut , Catherine Pikovsky
CPC分类号： F28D7/005 , F02C7/14 , F02K3/115 , F28F1/26 , F28F3/12 , F05D2260/213 , F28D2021/0021 , F28D2021/0049
摘要： The present invention relates to a bypass air/fluid heat exchanger (2) for a turbofan engine. According to the invention, this exchanger (2) comprises: —an annular outer shroud (3) with two walls, an inner wall (32) and an outer wall (31), —an annular inner shroud (4) concentric with the outer shroud (3), —a series of OGV guide vanes (5) which connect said outer shroud to said inner shroud, —and a circulation circuit (6) for circulating said fluid, the two shrouds delimiting a bypass air flow path, the fluid circulation circuit (6) is formed in the body of the outer shroud (3) and in the body of at least one of the OGV guide vanes (5), this circulation circuit (6) opening at the two respective ends thereof into an inlet opening (34) and into an outlet opening (35), formed through said outer wall (31) of the outer shroud, and the two shrouds (3, 4), the OGV guide vanes (5) and the circulation circuit (6) of said fluid are integral.
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