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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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公开(公告)号：US20220025772A1
公开(公告)日：2022-01-27
申请号：US17297041
申请日：2018-12-11
摘要： A unit cell (26) for use in a damping system (24) includes: an impacting structure (34); a cavity (32) encapsulating the impacting structure (34), the cavity (32) including a first hemisphere (32A) and a second hemisphere (32B), the cavity (32) disposed within a substrate (28), the substrate (28) forming an outer casing of the cavity (32); and at least one fluid (36) disposed in each of the first and second hemispheres (32A, 32B) between the impacting structure (34) and the outer casing (28).
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公开(公告)号：US20210254478A1
公开(公告)日：2021-08-19
申请号：US16794732
申请日：2020-02-19
发明人： Suryarghya Chakrabarti , Jing Li
IPC分类号： F01D5/26
摘要： A turbine damper may be provided that may include an elongated body sized to fit inside a turbine blade, the elongated body elongated along a radial direction of the turbine blade relative to a rotation axis of the turbine blade, and plural dampening masses coupled with the elongated body and disposed at different locations along the radial direction. The plural dampening masses may be one or more of sized to dampen different vibration modes of the turbine blade, or moveable relative to and along the elongated body in the radial direction.
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公开(公告)号：US10995632B2
公开(公告)日：2021-05-04
申请号：US16297936
申请日：2019-03-11
摘要： An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section extending in a spanwise direction, extending between a leading edge and a trailing edge in a chordwise direction, and extending in a thickness direction between a pressure side and a suction side. The airfoil section has a main body and a first skin. The main body includes a plurality of ribs defining a plurality of internal channels. The first skin is attached to the main body to enclose the plurality of internal channels such that the main body and the first skin cooperate to define the pressure and suction sides. A damper has at least one layer of damping material sandwiched between the first skin and the plurality of ribs. A method of forming a gas turbine engine component is also disclosed.
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公开(公告)号：US10982555B2
公开(公告)日：2021-04-20
申请号：US14787013
申请日：2014-02-27
发明人： Nicholas Aiello , John C. Duong
摘要： A root extending from a platform of an airfoil is disclosed. The root may include a first portion having a generally cylindrical shape, and a second portion extending from the first portion to the platform. The second portion may have a circumference larger than a circumference of the first portion.
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