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公开(公告)号：US20240133426A1
公开(公告)日：2024-04-25
申请号：US18400514
申请日：2023-12-29
CPC分类号： F16C27/045 , F01D5/26 , F01D25/164 , F05D2260/96
摘要： A rotor damping device for a turbomachine is provided. The rotor damping device includes a first fluid damper; and a second damper in communication with the first fluid damper, the second damper comprising a wire mesh, wherein the first fluid damper is transitionable between a working condition and an interruption condition, and wherein, during the interruption condition, the wire mesh of the second damper dampens vibration of the turbomachine.
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公开(公告)号：US11828191B2
公开(公告)日：2023-11-28
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
CPC分类号： F01D5/16 , F01D5/10 , F01D5/22 , F01D5/26 , F01D25/06 , F05D2220/30 , F05D2240/30 , F05D2260/96
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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公开(公告)号：US11815425B2
公开(公告)日：2023-11-14
申请号：US17450475
申请日：2021-10-11
申请人： IHI CORPORATION
发明人： Kensuke Shiomi , Kosuke Iwamoto , Teruyoshi Otoyo , Takashi Mori , Takaomi Inada
摘要： Provided is a jig for a vibration test of a rotor blade, for use in the vibration test for evaluating high cycle fatigue characteristics of the rotor blade for an aircraft engine, and the jig is provided with a jig body holding a dovetail portion of a fan blade and fixed onto an excitation table of a shaker, and a hydraulic jack that applies a load in a blade span direction to the fan blade to fix the fan blade to the jig body. Consequently, in the vibration test for evaluating the high cycle fatigue characteristics of the rotor blade, a test simulating an actual operation state can be carried out, the rotor blade can be efficiently excited to reach a large deformation region, and high cycle fatigue failure can occur without any increase in test cost.
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公开(公告)号：US11655719B2
公开(公告)日：2023-05-23
申请号：US17232721
申请日：2021-04-16
CPC分类号： F01D5/26 , F01D5/10 , F01D5/3046 , F01D5/3084 , F05D2240/11 , F05D2300/6033
摘要： An airfoil assembly for a turbine engine defines an axial direction, a radial direction, and a circumferential direction, and includes a first airfoil defining a first end along the radial direction, a first hub disposed on the first end of the first airfoil and having a first extension member extending at least partially in the radial direction, and a second airfoil adjacent to the first airfoil, the second airfoil defining a first end along the radial direction, a second hub disposed on the first end of the second airfoil and comprising a second extension member extending at least partially in the radial direction, and a circumferential bias assembly operable with the first extension member, the second extension member, or both for exerting a circumferential force on the first extension member, the second extension member, or both.
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公开(公告)号：US11466571B1
公开(公告)日：2022-10-11
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：US11421534B2
公开(公告)日：2022-08-23
申请号：US16221363
申请日：2018-12-14
发明人： Philippe Gerard Edmond Joly , Francois Jean Comin , Laurent Jablonski , Romain Nicolas Lagarde , Jean-Marc Claude Perrollaz
摘要： An assembly for a turbomachine including a first rotor module (2) with a first blade (20), and a second rotor module (3), connected to the first rotor module (2). The second rotor module includes a second blade with a smaller length than the first blade (20). A damping device (4) is attached to the second rotor module (3) and includes a radial external surface (40) supported with friction against the first module (2), 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：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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公开(公告)号：US11268526B2
公开(公告)日：2022-03-08
申请号：US14903996
申请日：2014-07-09
发明人： James T. Roach , Barry Barnett , Grant O. Cook, III , Charles R. Watson , Shari L. Bugaj , Glenn LeVasseur , Wendell V. Twelves, Jr. , Christopher J. Hertel , Colin J. Kling , Matthew A. Turner , JinQuan Xu , Steven Clarkson , Michael Caulfield
IPC分类号： F01D5/28 , F04D19/00 , F01D5/14 , B32B27/34 , B32B1/08 , B32B1/00 , B32B27/28 , B32B27/36 , F01D5/26 , F01D9/04 , F01D25/02 , F01D25/24 , F04D29/38 , F04D29/54
摘要： Plated polymeric gas turbine engine parts and methods for fabricating lightweight plated polymeric gas turbine engine parts are disclosed. The parts include a polymeric substrate plated with one or more metal layers. The polymeric material of the polymeric substrate may be structurally reinforced with materials that may include carbon, metal, or glass. The polymeric substrate may also include a plurality of layers to form a composite layup structure.
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公开(公告)号：US11248475B2
公开(公告)日：2022-02-15
申请号：US16709050
申请日：2019-12-10
摘要： Damper stacks, rotor blades, and turbomachines are provided. A rotor blade includes a main body including a shank and an airfoil extending radially outwardly from the shank. The rotor blade further includes a platform surrounding the main body, the platform comprising a slash face. The rotor blade further includes a damper stack disposed at the slash face and extending generally along an axial direction. The damper stack includes a plurality of damper pins, each of the plurality of damper pins being in contact with a neighboring damper pin.
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