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公开(公告)号：US20230139285A1
公开(公告)日：2023-05-04
申请号：US17907623
申请日：2021-03-22
发明人： Christophe Marcel Lucien PERDRIGEON , Didier Gabriel Bertrand DESOMBRE , Regis Eugene Henri SERVANT
摘要： Device for distributing oil from a rolling bearing (8) for an aircraft turbine engine, comprising: - a rolling bearing (8), an oil distributor ring (5) and - an annular track (26) of a dynamic seal (22), characterised in that it further comprises a nut (16) screwed on to a thread (5d) of the distributor ring and bearing axially against an axial end of the inner ring so as to clamp it axially, and in that the annular track is configured to bear axially against the distributor ring and comprises rotating locking elements (27) engaging with the additional elements (28)of the nut.
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公开(公告)号：US20200378311A1
公开(公告)日：2020-12-03
申请号：US16971106
申请日：2019-02-18
摘要： The invention relates to an assembly for holding (42) an epicyclic gear train in a turbomachine comprising an annular housing (50) in which are engaged a first annular part (44) and a second annular part (46) which are locked against rotation in the housing (50) by first annular interlocking means and second annular interlocking means, respectively, wherein: the first annular interlocking means are configured to allow a first circumferential clearance between the first annular part (44) and the housing (50); the second annular interlocking means are configured to allow a second circumferential clearance between the second annular part (48) and the housing (50); the first circumferential clearance is strictly less than the second circumferential clearance.
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3.发明公开公开(公告)号：US20230349343A1
公开(公告)日：2023-11-02
申请号：US18043749
申请日：2021-09-01
CPC分类号： F02K3/06 , F02C7/36 , F05D2260/40311 , F05D2220/36
摘要： An assembly for an aircraft turbine engine, includes a fan, a speed reduction gear and an intermediate casing including an internal annular structure that houses an epicyclic gear train equipped with a planet carrier. The assembly includes a secondary retention device for the ring gear of the planet carrier, the device including: first projections that project radially inwards from the internal annular structure, each first projection having a recess that is open radially inwards, axially downwards and circumferentially in a first direction; and second projections that project radially outwards from the ring gear of the planet carrier and cooperate with the first projections in such a way that each second projection is partially accommodated in the recess of the first projection with which it is associated and downstream therefrom.
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公开(公告)号：US20220010688A1
公开(公告)日：2022-01-13
申请号：US17294335
申请日：2019-11-14
摘要： The invention concerns a device for centring and guiding in rotation a rotating part rotating about a turbomachine axis, comprising a rolling bearing comprising an outer ring, a bearing support surrounding the outer ring, an annular attachment flange mounted on the bearing support and a flexible portion connecting the outer ring to the attachment flange and comprising first arms extending from the attachment flange in a first direction with a first radial component towards the inside, second arms extending from the outer ring of the rolling bearing in a second direction with a second radial component opposite the first radial component, towards the outside, and an annular base that the first arms and the second arms join; the first arms alternating circumferentially with the second arms.
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公开(公告)号：US20230407763A1
公开(公告)日：2023-12-21
申请号：US18029783
申请日：2021-09-24
发明人： Christophe Marcel Lucien PERDRIGEON , Didier Gabriel Bertrand DESOMBRE , Régis Eugène Henri SERVANT
CPC分类号： F01D25/18 , F02C7/06 , F02C7/36 , F05D2220/32 , F05D2240/14 , F05D2240/50 , F05D2260/98
摘要： Stator structure (22) extending around an axis of the turbomachine and comprising: —a support (50) having an inner surface centred on the axis and —a flange (60) defining an air chamber (A2) and having an outer surface centred on the axis, the support (50) extending around the flange (60) such that the inner and outer surfaces are opposite to each other, the structure (22) defining an oil circuit and an air circuit which are formed by upstream channels (64, 65) and downstream channels (54, 55), —each upstream channel (64, 65) defining an outer opening in the outer surface, —each downstream channel (54, 55) defining an inner opening in the inner surface, each circuit being oriented between the outer and inner openings in a direction comprising a component radial to the axis.
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公开(公告)号：US20220340290A1
公开(公告)日：2022-10-27
申请号：US17754078
申请日：2020-09-25
摘要： The invention concerns an aircraft turbine engine (1), comprising a gas generator comprising at least one annular gas flow duct (2), the duct (2) being defined by two annular housings, respectively an external housing (3b) and an internal housing (3a), extending one around the other and connected together by at least one tubular arm (5) for the passage of a lubricating oil line (7). According to the invention, the line (7) comprises a first fixed section (14) secured to the external housing (3b), a second fixed section (16) secured to a piece of equipment (4) of the turbomachine capable of moving or vibrating during operation relative to the housings (3a, 3b). and an intermediate section (18) connecting the first and second sections (14, 16), this intermediate section (18) having a generally elongate shape and comprising longitudinal ends engaged and capable of swiveling and/or sliding in ends of the first and second sections (14, 16).
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公开(公告)号：US20220316584A1
公开(公告)日：2022-10-06
申请号：US17596045
申请日：2020-05-29
摘要： A planetary reduction gear (10) for an aircraft turbine engine, said reduction gear comprising a rotatable sun gear, a rotatable ring gear (9) and satellite gears meshed with the sun gear and the ring gear and carried by a planet carrier intended to be fixed to a stator, the reduction gear further comprising an annular trough for recovering and channelling lubrication oil that is mounted around the ring gear, characterised in that the reduction gear further comprises an annular deflector (22) fixed to the ring gear and configured to route the oil exiting radially towards the outside of the ring gear up to the trough by virtue of centrifugal forces, the trough comprising an annular chamber (18) which is axially remote relative to a median plane (P) substantially passing through the centre of the ring gear, and an annular duct (20) located on a side of said chamber and emerging in said chamber.
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公开(公告)号：US20240151149A1
公开(公告)日：2024-05-09
申请号：US18549415
申请日：2022-03-15
发明人： Paul Ghislain Albert LEVISSE , Caroline Marie FRANTZ , Didier Gabriel Bertrand DESOMBRE , Christophe Marcel Lucien PERDRIGEON , Jean-Claude Christian TAILLANT
CPC分类号： F01D7/02 , F01D25/16 , F05D2220/323 , F05D2240/30 , F05D2260/60
摘要： A fan module for an aircraft turbine engine, the module including a fan having variable-pitch blades and an oil transfer device for transferring oil between a stator and a rotor, the device including a stator ring having a cylindrical inner surface and internal oil ducts and a shaft engaged in the ring and having a cylindrical outer surface and internal oil ducts; the device includes a plain bearing located between said cylindrical inner surface and the cylindrical outer surface and defined by a single band; and rolling bearings mounted between the ring and the shaft, on either side of the plain bearing, each of these rolling bearings having one of the rings thereof integrated in one of the elements selected from the ring and the shaft.
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公开(公告)号：US20230313739A1
公开(公告)日：2023-10-05
申请号：US17905318
申请日：2021-03-26
发明人： Julien Fabien Patrick BECOULET , Didier Gabriel Bertrand DESOMBRE , Matthieu Bruno Francois FOGLIA
摘要： The invention relates to a turbine engine module, comprising: - a fan shaft (6), - a power shaft (15) rotating the fan shaft via a speed reducer (21) arranged in a lubrication chamber (22), - a lubrication system (50) for the speed reducer (21) having a main circuit (51), which is closed, for supplying the lubrication chamber, and an auxiliary circuit (60), which is closed, for supplying the lubrication chamber when the main circuit is inactive, the auxiliary circuit comprising an auxiliary pump (61) driven by an electric motor (63), and - an electric machine (65) configured to power the electric motor (63), the electric machine having a rotor connected to the fan shaft in order to be rotated and a stator mounted on a stationary member at least partially supporting the electric machine.
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公开(公告)号：US20230057973A1
公开(公告)日：2023-02-23
申请号：US17799539
申请日：2021-02-11
摘要： The present invention relates to a shaft for a propulsion system configured to rotate a reducing mechanism about a rotational axis, the shaft comprising: —a first end configured to engage with an input gear of the reducing mechanism, —a first bellows and a second bellows, the first bellows and the second bellows being rotationally symmetrical about the rotational axis, the first bellows extending between the first end and the second bellows, and —a frustoconical body mechanically connecting the first bellows and the second bellows.
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