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公开(公告)号：US20230286644A1
公开(公告)日：2023-09-14
申请号：US18006128
申请日：2021-07-15
发明人： Clément COTTET , Vivien Mickaël COURTIER , Vincent JOUDON , Arnaud LANGLOIS , Régis Eugène Henri SERVANT , Laurent JABLONSKI
CPC分类号： B64C11/30 , F01D7/00 , F01D5/30 , B64C11/06 , F05D2260/70
摘要： An assembly including a propeller blade and a pitch adjustment system for setting the pitch of the blade. A root of the blade has a bulb and the pitch adjustment system for setting the pitch of the blade includes a cup having an upper opening; a retaining ring, which extends around the bulb, is restricted at least in terms of axial movement towards the opening relative to the cup and has a bearing face to inhibit axial movement of the root towards the opening The pitch adjustment system being further includes a lower seat for the root to engage the cup, the seat and/or the retaining ring being mounted so as to be capable of axial translation relative to the cup by at least one clamping mechanism.
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公开(公告)号：US20210079794A1
公开(公告)日：2021-03-18
申请号：US16954007
申请日：2018-12-14
发明人： Philippe Gérard Edmond JOLY , François Jean COMIN , Charles Jean-Pierre DOUGUET , Laurent JABLONSKI , Romain Nicolas LAGARDE , Jean Marc Claude PERROLLAZ
摘要： The invention relates to a turbomachine assembly (1) comprising: a first rotor module (2) comprising a first blade (20), a second rotor module (3), connected to the first rotor module (2), and comprising a second blade of smaller length than the first blade (20), and a damping device (4) comprising a first radial external surfaces (41) supported with friction against the first module (2), as well as a second radial external surface (42) supported with friction against the second module (3), so as to couple the modules (2, 3) for the purpose of damping their respective vibrational movements during operation.
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公开(公告)号：US20190186276A1
公开(公告)日：2019-06-20
申请号：US16219823
申请日：2018-12-13
发明人： Philippe Gerard Edmond JOLY , Francois Jean COMIN , Laurent JABLONSKI , Romain Nicolas LAGARDE , Jean-Marc Claude PERROLLAZ , Charles Jean-Pierre Douguet
CPC分类号： F01D5/22 , F01D5/10 , F01D5/3007 , F05D2240/80 , F05D2260/96
摘要： The invention relates to a turbomachine assembly (1) comprising: a first rotor module (2) comprising a disk (21), a first blade (20) being mounted on the external periphery of the disk (21), the first blade (20) comprising a platform (25) and a support (27), a second rotor module (3), connected to the first rotor module (2) by means of at least two attachments (22) and comprising a second blade of smaller length than the first blade (20), and a damping device (4) attached to the attachment (22) between the first (2) and the second (3) rotor module so as to dampen their vibrational movements during operation, and comprising: a head (40) comprising a first radial external surface (42) supported with friction against the platform (25), and two attachment feet (41) extending on either side of the support (27) of the first blade (20).
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公开(公告)号：US20230294817A1
公开(公告)日：2023-09-21
申请号：US18006350
申请日：2021-07-15
发明人： Vincent JOUDON , Clément COTTET , Vivien Mickaël COURTIER , Laurent JABLONSKI , Régis Eugène Henri SERVANT
CPC分类号： B64C11/30 , F01D7/00 , F01D5/30 , F05D2260/70
摘要： Disclosed is a variable pitch propeller blade for an aircraft turbine engine. The blade includes an airfoil connected to a root, the root having a body housed in an annular barrel that extends around a pitch axis of the blade, the body including a free end opposite the airfoil; a shoulder towards the airfoil; and a bulb located between the free end and the shoulder. The bulb can have a cross-section, referred to as the middle section, that has a maximum value Sm, and the barrel can be affixed to the body and covers and matches at least a portion of the bulb and the shoulder.
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公开(公告)号：US20230038378A1
公开(公告)日：2023-02-09
申请号：US17758731
申请日：2021-01-06
IPC分类号： F02C7/36
摘要： An assembly for a turbine engine extending along an axis, includes a stator, a low-pressure compressor shaft, a low-pressure compressor comprising a rotor comprising a drum rotatably coupled to the shaft of the low-pressure compressor, and a fan comprising a disk rotatably coupled to the shaft of the low-pressure compressor. The drum has a radially internal part rotatably coupled to the shaft of the low-pressure compressor and a radially external part fixed to the radially internal part by means of detachable fixing means. A first axial retention means is configured to axially and detachably retain the disk of the fan relative to the shaft of the low-pressure compressor. A second axial retention means is configured to axially and detachably retain the radially internal part of the drum relative to the shaft of the low-pressure compressor.
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公开(公告)号：US20210010391A1
公开(公告)日：2021-01-14
申请号：US16955518
申请日：2018-12-18
发明人： Philippe Gérard Edmond JOLY , François Jean COMIN , Charles Jean-Pierre DOUGUET , Laurent JABLONSKI , Romain Nicolas LAGARDE , Jean-Marc Claude PERROLLAZ
IPC分类号： F01D25/06
摘要： The invention relates to an assembly (1) for a turbomachine comprising: a first rotor module (2) comprising a first blade (20), a second rotor module (3), connected to the first rotor module (2), and comprising a second blade with a length less than the first blade (20), and a damping device (4) extending with at least one component along a turbomachine longitudinal axis (X-X), characterized in that the damping device (4) is annular while extending circumferentially around the turbomachine longitudinal axis (X-X) and in that the damping device (4) comprises a first radial external surface (40) supported with friction against the first module (2) as well as a second radial external surface (42) supported with friction against the second module (3), so as to couple the modules (2, 3) in order to damp their respective vibrational movements during operation.
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公开(公告)号：US20230286649A1
公开(公告)日：2023-09-14
申请号：US18006344
申请日：2021-07-15
发明人： Clement COTTET , Vivien Mickael COURTIER , Vincent JOUDON , Regis Eugene Henri SERVANT , Laurent JABLONSKI
摘要： An assembly comprising a propeller blade and its system for angularly adjusting the pitch of the blade including a bowl which is radially delimited by an annular wall (44)-extending about an axis for adjusting the pitch of the blade, the bowl having a bottom wall, a free lower end of the root being fitted axially into a complementary housing of the bottom wall in order to rotatably connect the bowl and the blade about the pitch-adjustment axis. The root of the blade comprises a first limiting face that engages with a first abutment face of the bowl to limit the rotation of the blade in the event of breakage of the lower end of the root.
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公开(公告)号：US20220299040A1
公开(公告)日：2022-09-22
申请号：US16221910
申请日：2018-12-17
发明人： Philippe Gerard Edmond JOLY , Marie-Oceane PARENT , Francois Jean COMIN , Romain Nicolas LAGARDE , Jean-Marc Claude PERROLLAZ , Laurent JABLONSKI , Charles Jean-Pierre DOUGUET
摘要： A turbomachine assembly is provided. The assembly includes: a first rotor module including a first blade, a second rotor module, connected to the first rotor module, and including a second blade of smaller length than the first blade, and a damping device including a plurality of first radial external surfaces supported with friction against the first module. The damping device is stepped, and includes a second radial external surface supported with friction against the second module, so as to couple the modules for the purpose of damping their respective vibrational movements during operation.
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公开(公告)号：US20220228495A1
公开(公告)日：2022-07-21
申请号：US17614812
申请日：2020-05-27
发明人： Philippe Gérard Edmond JOLY , Romain Nicolas LAGARDE , Jean-Marc Claude PERROLLAZ , Laurent JABLONSKI , François Jean COMIN , Edouard Antoine Dominique Marie DE JAEGHERE , Charles Jean-Pierre DOUGUET
摘要： The present invention relates to a turbomachine assembly, comprising: a casing (10), a first rotor (12) which is movable in rotation with respect to the casing (10) about a longitudinal axis (X-X), and comprising: *a disk (120), and *a plurality of blades (122) capable of flapping with respect to the disk (120) during a rotation of the first rotor (12) with respect to the casing (10), a second rotor (140) which is movable in rotation with respect to the casing (10) about the longitudinal axis (X-X), and a damper (2) which is configured to damp a displacement of the first rotor (12) with respect to the second rotor (140) in a plane orthogonal to the longitudinal axis (X-X), the displacement being caused by a flapping of at least one blade (122) among the plurality of blades (122), the damper (2) comprising: o a first bearing part (21): *bearing against the first rotor (12), and *being configured to apply a first centrifugal force (C1) to the first rotor (12), o a second bearing part (22): *bearing against the second rotor (140), and *being configured to apply a second centrifugal force (C2) on the second rotor (140), and o a linking part (20): *connecting the first bearing part (21) to the second bearing part (22), and being thinned relative to the first bearing part (21) and the second bearing part (22), and o a flyweight (3) which is fixedly mounted on the damper (2).
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公开(公告)号：US20220228491A1
公开(公告)日：2022-07-21
申请号：US17614226
申请日：2020-05-27
发明人： Philippe Gérard Edmond JOLY , Romain Nicolas LAGARDE , Jean-Marc Claude PERROLLAZ , Laurent JABLONSKI , François Jean COMIN , Edouard Antoine Dominique Marie DE JAEGHERE , Charles Jean-Pierre DOUGUET
摘要： A turbomachine assembly includes a casing, first and second rotors, and a damper. The first rotor includes a disk and blades and is movable in rotation relative to the casing. The second rotor is movable relative to the casing around a longitudinal axis. The damper damps a movement of the first rotor relative to the second rotor. The damper includes first to third parts. The first part bears on the first rotor in a first area extending over a first angular sector around the longitudinal axis and applies a first centrifugal force on the first rotor. The second part bears on the first rotor in a second area that is smaller than the first angular sector and extends over a second angular sector around the longitudinal axis. The third part bears on the second rotor and applies a second centrifugal force on the second rotor.
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