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公开(公告)号：US20180016931A1
公开(公告)日：2018-01-18
申请号：US15645504
申请日：2017-07-10
发明人： Kamel Benderradji , Blaise Bergan , Alain Marc Lucien Bromann , Suzanne Madeleine Coustillas , Lilian Yann Dumas
CPC分类号： F01D17/141 , F01D9/041 , F01D17/162 , F01D17/26 , F04D29/563 , F05D2220/323 , F05D2260/50 , Y02T50/671
摘要： An assembly, in particular for controlling variable pitch vanes in a turbine engine, comprising an actuating ring surrounding a casing of the turbine engine and connected by rods to variable pitch vanes, in addition to a driving means for rotating the actuating ring around the casing. The assembly includes a slidingly connected passive element, one end of which is connected by a sliding pivoting link on the actuating ring and a second end is connected by a ball-joint link to the casing.
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公开(公告)号：US20190309649A1
公开(公告)日：2019-10-10
申请号：US16374216
申请日：2019-04-03
摘要： The present disclosure relates to a control device of an annular row of variable-pitch vanes for an aircraft engine. The device may include an annular row of actuating levers which each may include a first end attached to a pivot of one of the vanes and a second end connected to a control ring in rotation about an axis of rotation. The control ring may include at least one annular series of articulated links, wherein the second end of each lever carries a pivot connection articulating two successive links of the annular series about a single axis, the single axis extending in a direction substantially parallel to the axis of rotation.
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公开(公告)号：US10330021B2
公开(公告)日：2019-06-25
申请号：US14877270
申请日：2015-10-07
发明人： Kamel Benderradji , Alain Marc Lucien Bromann , Lilian Yann Dumas , Pamela Dominique Daniele Reichert
摘要： A system for controlling variable-pitch vanes for a turbine engine, including a control ring having an axis of revolution and, about the axis of revolution, an annular row of connecting rods for connecting the ring to the vanes, each connecting rod including a first end designed so as to be connected to one of the vanes, and a second end which is connected to an elongate shaft which is connected to s the ring. The shaft connected to each connecting rod has an axis of elongation which is inclined relative to a plane extending substantially through the axis of revolution and the connecting rod.
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公开(公告)号：US11808160B2
公开(公告)日：2023-11-07
申请号：US17435428
申请日：2020-03-02
发明人： Romain Nicolas Lagarde , Marie-Charline Stéphanie Charbonnier , Jean-Marc Claude Perrollaz , Lilian Yann Dumas
IPC分类号： F01D25/16
CPC分类号： F01D25/162 , F05D2220/32 , F05D2230/60 , F05D2230/70 , F05D2240/54
摘要： A sub-assembly of a turbine engine including a shaft, a bearing for guiding an axial end of the shaft, a nut which is screw-connected to the end of the shaft and a member for blocking the rotation of the nut in relation to the end of the shaft, wherein the member for blocking the nut includes a first section bearing a plurality of flexible tabs, one end of each tab of which cooperates with a radially inner annular wall of the end of the shaft and includes a second section which cooperates with the nut, characterised in that the second section of the blocking member is screw-connected to the nut and the features of the thread between the blocking member and the nut are different from the features of the thread between the nut and the end of the shaft.
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公开(公告)号：US11015477B2
公开(公告)日：2021-05-25
申请号：US16448680
申请日：2019-06-21
摘要： An assembly for the control of variable pitch blades. The assembly includes a movable part movable parallel to an axis is in engagement with pivot connections which rotate about at least one radial axis fixed with respect to the casing, and which act on a radial shaft, which passes through a clevis fixed with a control ring to rotate with it about said axis. The radial shaft is mounted radially rotating with respect to the control ring and the casing.
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公开(公告)号：US11047255B2
公开(公告)日：2021-06-29
申请号：US16374216
申请日：2019-04-03
摘要： The present disclosure relates to a control device of an annular row of variable-pitch vanes for an aircraft engine. The device may include an annular row of actuating levers which each may include a first end attached to a pivot of one of the vanes and a second end connected to a control ring in rotation about an axis of rotation. The control ring may include at least one annular series of articulated links, wherein the second end of each lever carries a pivot connection articulating two successive links of the annular series about a single axis, the single axis extending in a direction substantially parallel to the axis of rotation.
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公开(公告)号：US10927699B2
公开(公告)日：2021-02-23
申请号：US15741479
申请日：2016-06-27
发明人： Alain Marc Lucien Bromann , Kamel Benderradji , Lilian Yann Dumas , Blaise Bergon , Suzanne Madeleine Coustillas
摘要： Variable-pitch blade control ring (44) for a turbine engine, including an annular body (42) configured to be mounted so as to be rotatable about an annular casing (16) of the turbine engine. The body links to levers (34) for connecting to the vanes. The ring has a mechanism for guiding in an axial and/or helical direction, supported by the body. The mechanism includes at least one substantially radial finger (60, 62) for axial abutment on at least one first surface (72, 74) of the casing and for sliding on the surface.
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公开(公告)号：US20190390563A1
公开(公告)日：2019-12-26
申请号：US16448680
申请日：2019-06-21
摘要： An assembly for the control of variable pitch blades. The assembly includes a movable part movable parallel to an axis is in engagement with pivot connections which rotate about at least one radial axis fixed with respect to the casing, and which act on a radial shaft, which passes through a clevis fixed with a control ring to rotate with it about said axis. The radial shaft is mounted radially rotating with respect to the control ring and the casing.
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公开(公告)号：US11952950B2
公开(公告)日：2024-04-09
申请号：US17628608
申请日：2020-07-23
CPC分类号： F02C9/20 , F01D17/162 , F02C6/08 , F02C9/18 , F04D27/023 , F04D29/563
摘要： An axial turbomachine comprising a compression device with a variable-orientation vane rectifier stage; a combustion chamber downstream of the compression device; a turbine device downstream of the combustion chamber; and a leak passage of air compressed by the compression device, between the compression device and the turbine device for cooling the turbine device; and where the rectifier stage is configured to modulate the section of the leak passage according to the orientation of the vanes of the stage.
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10.发明授权公开(公告)号：US11859508B2
公开(公告)日：2024-01-02
申请号：US17628523
申请日：2020-07-10
发明人： Thomas Nolwenn Emmanuel Delahaye , Blaise Bergon , Laurent Jablonski , Lilian Yann Dumas , Thomas Etienne Camille Marie Van De Kerckhove , Noël Joseph Camille Robin , Guillaume Sevi
CPC分类号： F01D25/246 , F01D9/042 , F05D2220/323 , F05D2240/12 , F05D2240/14 , F05D2260/30
摘要： Disclosed is a compressor of a dual-flow aircraft turboshaft engine extending longitudinally along an axis X, the compressor comprising a low-pressure compressor, a high-pressure compressor and an intermediate casing axially connecting the low-pressure compressor and the high-pressure compressor, the high-pressure compressor comprising an inlet guide stator comprising a retaining ring, an outer high-pressure compressor casing and a plurality of vanes, the compressor comprising an immobilising device comprising at least one first member secured to the intermediate casing and at least one second member secured to the retaining ring and configured to cooperate with the first member in order to prevent tangential movement while allowing axial movement and radial movement of the retaining ring relative to the intermediate casing according to the axis X.
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