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公开(公告)号:US11585236B2
公开(公告)日:2023-02-21
申请号:US16982795
申请日:2019-03-20
发明人: Dimitri Daniel Gabriel Marquie , Adrien Jacques Philippe Fabre , Frédéric Patard , Pierre Jean-Baptiste Metge
摘要: A bearing support designed to be secured to a stationary turbojet element for supporting a journal, including a cone which widens from a central portion for supporting the journal to a portion for securing to the stationary element, a cylindrical body extending the portion for securing to the stationary element while surrounding the cone, an upstream skirt carried by the cone for defining an upstream enclosure for the central portion, and at least one downstream revolution element carried by the cone for defining a downstream enclosure for the central portion. The bearing support can be made as a single part produced by additive manufacturing.
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公开(公告)号:US10648406B2
公开(公告)日:2020-05-12
申请号:US15683394
申请日:2017-08-22
发明人: Sébastien Emile Philippe Tajan , Eddy Keomorakott Souryavongsa , Regis Eugéne Henri Servant , Adrien Jacques Philippe Fabre , Stephane Ibarzo
摘要: A controller for controlling a system for changing the pitch of blades of a turbine engine propeller, the controller includes a fixed member (28) and a member (29) which is movable in translation along a longitudinal axis (X) relative to the fixed member (28), and an anti-rotation device (33) configured so as to prevent the rotation of the movable member (29) relative to the fixed member (28) about the axis (X). The anti-rotation device includes a longitudinal structural crossmember (35) which is mounted by a first and a second end (36, 37) on the fixed member, and support and guide unit (57) integrally in translation the movable member along the axis (X), the crossmember extending radially outside the movable member and the fixed member relative to a radial axis (Y) which is perpendicular to the axis (X) and being guided through the support and guide unit.
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公开(公告)号:US11280273B2
公开(公告)日:2022-03-22
申请号:US16677461
申请日:2019-11-07
摘要: The invention relates to a bellcrank for a turbomachine having a first bore, a second bore and a third bore, the first bore being connected to the second bore by a first branch, the second bore being connected to the third bore by a second branch, the third bore being connected to the first bore by a third branch, a fourth branch connecting the first branch to the second branch.
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4.
公开(公告)号:US20180043991A1
公开(公告)日:2018-02-15
申请号:US15672763
申请日:2017-08-09
发明人: Sébastien Emile Philippe Tajan , Adrien Jacques Philippe Fabre , Paul Antoine Foresto , Régis Eugène Henri Servant , Stéphane Ibarzo
IPC分类号: B64C11/38
CPC分类号: B64C11/38 , B64C11/30 , B64C11/306 , Y02T50/66
摘要: A system is configured to change the pitch of blades of at least one turbine engine propeller provided with multiple blades. The system includes a control means acting on a connecting mechanism connected to the blades of the propeller. The control means includes a stationary body and a movable body translatable along a longitudinal axis (X) relative to the stationary body and defining two chambers. A fluid supply means is configured to be connected to a fluid supply source and to supply the chambers. The fluid supply means includes at least one channel. The channel is arranged and extends along an axis (Q) parallel to the longitudinal axis in an overthickness of a wall of the stationary body, the overthickness extending radially inside relative to the longitudinal axis.
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公开(公告)号:US20180043990A1
公开(公告)日:2018-02-15
申请号:US15673322
申请日:2017-08-09
发明人: Sébastien Emile Philippe Tajan , Gilles Alain Marie Charier , Clément Cottet , Adrien Jacques Philippe Fabre , Christophe Marcel Lucien Perdrigeon
CPC分类号: B64C11/32 , B64C11/30 , B64D2027/005 , F01D7/00 , F01D25/16 , F05D2220/323 , F05D2260/79 , Y02T50/66
摘要: The invention relates to turbine engine module (1) including a case (9) rotating around a longitudinal axis (X) and carrying a propeller having a plurality of blades, a stationary case (15) comprising a cylindrical wall (16) extending between an inner wall (17) and an outer wall (18) of the rotating case (9), and a system (26) for changing the pitch of the blades (14) of the propeller. The wall (16) is connected downstream to a first substantially frustoconical wall (42) and upstream to a second substantially frustoconical wall (41), a first rolling bearing (19) being inserted respectively downstream directly between a radially outer face (21) of the inner wall (17) and a radially inner face (23) of the first frustoconical wall, and a second rolling bearing (19′) inserted downstream directly between the radially outer face (21) of the inner wall (17) and an inner face (43) of the second frustoconical wall (41).
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6.
公开(公告)号:US20170166295A1
公开(公告)日:2017-06-15
申请号:US15116868
申请日:2015-02-10
发明人: Charles-Henri Michel Marie Derrez , Adrien Jacques Philippe Fabre , Christophe Paul Jacquemard , Régis Eugène Henri Servant , Sébastien Emile Philippe Tajan
摘要: The invention relates to a device (12) for a non-streamlined propeller (6, 7) with blades (10) having variable pitch of a turbomachine (1), the device comprising a support (15) intended to support a blade (10) and including a cylindrical foot (17), a bearing comprising a radially internal annular section (20) and a radially external annular section (21) capable of pivoting with respect to each other, the foot (17) being mounted in said internal section (20) of the bearing. The device comprises a hub (27) mounted in the foot (17), said hub (27) including a rim (29) comprising a face (30) coming to bear on the radially internal annular section (20) of the bearing, the hub (27) and the foot (17) of the support (15) comprising complementary engagement elements (18, 28) interacting with a locking component (23).
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公开(公告)号:US10830076B2
公开(公告)日:2020-11-10
申请号:US16270771
申请日:2019-02-08
发明人: Cedric Zaccardi , Christophe Marcel Lucien Perdrigeon , Paul Antoine Foresto , Adrien Jacques Philippe Fabre
摘要: A guide vane located in a fan air flow in an aircraft twin-spool turbomachine, the vane being made with an extrados body and an intrados body between which there is a thermal conduction matrix. Furthermore, the attachment devices between the two spools are arranged outside the aerodynamic part of the vane.
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公开(公告)号:US10669010B2
公开(公告)日:2020-06-02
申请号:US15569639
申请日:2016-04-25
发明人: Sébastien Emile Philippe Tajan , Adrien Jacques Philippe Fabre , Adrien Louis Nicolas Laurenceau , Jonathan Evert Vlastuin , Laurence Francine Vion
摘要: The invention relates to an unducted-fan aircraft engine comprising a generally cylindrical nacelle through which a primary jet flows, the nacelle bearing a fan rotor comprising variable-pitch vanes (33) located radially outside the nacelle in order to be traversed by a secondary jet (31) flowing longitudinally around the nacelle. The rotor comprises a hub bearing variable-pitch vane supports each carrying one vane (33), each vane (33) comprising a blade extending from a root that is used to removably attach same to a base of the associated support (34). Each base (36) is located radially outside the nacelle so that it is in the secondary jet, and each assembly formed by a base (36) and the vane root supported by the base (36) is surrounded and covered by a detachable aerodynamic cover (37).
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公开(公告)号:US10604235B2
公开(公告)日:2020-03-31
申请号:US15673322
申请日:2017-08-09
发明人: Sébastien Emile Philippe Tajan , Gilles Alain Marie Charier , Clément Cottet , Adrien Jacques Philippe Fabre , Christophe Marcel Lucien Perdrigeon
摘要: The invention relates to turbine engine module (1) including a case (9) rotating around a longitudinal axis (X) and carrying a propeller having a plurality of blades, a stationary case (15) comprising a cylindrical wall (16) extending between an inner wall (17) and an outer wall (18) of the rotating case (9), and a system (26) for changing the pitch of the blades (14) of the propeller. The wall (16) is connected downstream to a first frustoconical wall (42) and upstream to a second frustoconical wall (41), a first rolling bearing (19) being inserted respectively downstream directly between a radially outer face (21) of the inner wall (17) and a radially inner face (23) of the first frustoconical wall, and a second rolling bearing (19′) inserted downstream directly between the radially outer face (21) of the inner wall (17) and an inner face (43) of the second frustoconical wall (41).
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公开(公告)号:US20180058324A1
公开(公告)日:2018-03-01
申请号:US15683394
申请日:2017-08-22
发明人: Sébastien Emile Philippe TAJAN , Eddy Keomorakott Souryavongsa , Regis Eugéne Henri Servant , Adrien Jacques Philippe Fabre , Stephane Ibarzo
CPC分类号: F02C7/06 , B64C11/303 , B64C11/32 , B64D27/10 , F01D25/18 , F05D2220/323 , F05D2240/54 , F05D2260/98 , Y02T50/66
摘要: The invention relates to a means (27) for controlling a system for changing the pitch of blades of a turbine engine propeller, the control means (27) comprising a fixed member (28) and a member (29) which is movable in translation along a longitudinal axis (X) relative to the fixed member (28), and an anti-rotation device (33) configured so as to prevent the rotation of the movable member (29) relative to the fixed member (28) about the axis (X).According to the invention, the anti-rotation device comprises a longitudinal structural crossmember (35) which is mounted by means of a first and a second end (36, 37) on the fixed member, and support and guide means (57) integrally in translation the movable member along the axis (X), the crossmember extending radially outside the movable member and the fixed member relative to a radial axis (Y) which is perpendicular to the axis (X) and being guided through the support and guide means.
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