公开(公告)号：US20240240651A1

公开(公告)日：2024-07-18

申请号：US18618118

申请日：2024-03-27

Applicant: General Electric Company

Inventor： Narayanan Payyoor ,  Peeyush Pankaj

IPC: F04D29/66 ,  F01D25/16 ,  F04D29/053 ,  F04D29/059 ,  F16C19/52 ,  F16C27/04 ,  F16C35/07 ,  F16C35/077

CPC classification number: F04D29/668 ,  F01D25/164 ,  F04D29/053 ,  F04D29/059 ,  F16C19/527 ,  F16C27/045 ,  F16C35/07 ,  F16C35/077 ,  F05D2250/36 ,  F05D2260/96 ,  F16C2360/23

Abstract: Damping devices, turbomachines, and methods of damping vibration are provided. For example, a damping device for damping vibration of a shaft rotatable about an axis of rotation is provided. The damping device defines radial and axial directions. The damping device comprises a bearing, a housing, and a damper element. The housing and damper element define a cavity therebetween for receipt of a damping fluid. The cavity has a length along the axial direction that is curved away from the axis of rotation. As another example, a turbomachine comprising a shaft rotatable about an axis of rotation includes a damping device positioned annularly about the shaft. The damping device comprises a housing and a damper element defining a cavity therebetween for receipt of a damping fluid that has a curved shape. The cavity is curved in a plane extending along the radial and axial directions and including the axis of rotation.

公开(公告)号：US12012960B2

公开(公告)日：2024-06-18

申请号：US17765911

申请日：2020-12-15

Applicant: ATLAS COPCO AIRPOWER, NAAMLOZE VENNOOTSCHAP

Inventor： Bjorn Verrelst ,  Nils Vercauteren ,  Stijn Pittois ,  Axel Van De Walle

IPC: F04C18/16 ,  F01C21/02 ,  F01D25/16 ,  F16C19/06 ,  F16C27/08

CPC classification number: F04C18/16 ,  F01C21/02 ,  F01D25/164 ,  F16C27/08 ,  F04C2240/50 ,  F04C2240/52 ,  F04C2240/56 ,  F05C2225/02 ,  F05C2251/02 ,  F16C19/06 ,  F16C2360/43

Abstract: Compressor device provided with at least one compressor element and a drive for the compressor element, wherein all bearings of at least one shaft in the compressor device configured to carry static axial load, are provided with a bearing damper which comprises a coupling element and at least one damping element made of damping elastomer material. The bearing damper is installed with the aid of the coupling element between a bearing of the compressor device and the housing of the compressor device. The coupling element allows little or no movement of the bearing relative to the housing the radial direction compared to the axial direction. The damping element is configured to dampen the axial movement of the bearing relative to the housing.

公开(公告)号：US11976593B1

公开(公告)日：2024-05-07

申请号：US18049112

申请日：2022-10-24

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  Kudum Shinde ,  Surender Reddy Bhavanam ,  Weize Kang

IPC: F01D25/16 ,  F02C7/06 ,  F16C19/54 ,  F16C25/08 ,  F16C27/06

CPC classification number: F02C7/06 ,  F01D25/16 ,  F01D25/162 ,  F01D25/164 ,  F05D2220/32 ,  F05D2240/52 ,  F16C19/54 ,  F16C19/541 ,  F16C25/083 ,  F16C27/066 ,  F16C2360/23

Abstract: A gas turbine engine including a rotating shaft and a bearing assembly. The bearing assembly is configured to support the rotating shaft. The bearing assembly has a first bearing and a second bearing. The first bearing is configured to support an axial load of the rotating shaft when a forward thrust of the rotating shaft is greater than ten percent. The second bearing is configured to support the axial load of the rotating shaft when a thrust of the rotating shaft is between ten percent forward thrust and ten percent aft thrust, inclusive of the end points.

公开(公告)号：US20240133426A1

公开(公告)日：2024-04-25

申请号：US18400514

申请日：2023-12-29

Applicant: General Electric Company

Inventor： Richard Schmidt ,  Narayanan Payyoor ,  Peeyush Pankaj

IPC: F16C27/04 ,  F01D5/26 ,  F01D25/16

CPC classification number: F16C27/045 ,  F01D5/26 ,  F01D25/164 ,  F05D2260/96

Abstract: 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.

公开(公告)号：US11846318B2

公开(公告)日：2023-12-19

申请号：US17625472

申请日：2020-02-06

Applicant: LORD Corporation

Inventor： Mark R. Jolly ,  Victor M. Zaccardo ,  Paul R. Black ,  Daniel E. Kakaley ,  Russell E. Altieri

IPC: F16C27/04 ,  F16C32/04 ,  F01D25/16 ,  F16C19/06 ,  F16F15/023

CPC classification number: F16C27/045 ,  F01D25/164 ,  F16C19/06 ,  F16C32/0402 ,  F16F15/0237 ,  F05D2240/54 ,  F05D2260/96 ,  F16C2360/23

Abstract: A system for controlling shaft displacement within a support structure, the system having a rotatable shaft, at least one bearing supporting the shaft, the at least one bearing having an inner race rotatable along with the shaft and an outer race circumferentially surrounding the inner race, an electromagnet assembly positioned about the shaft along a longitudinal axis thereof, and a controller that detects a radial motion of the shaft and determines a corrective force to reduce the radial motion of, or a parameter related to, the shaft, the controller commanding the electromagnet assembly to generate the corrective force to act on the shaft, the electromagnet assembly having a plurality of phases spaced circumferentially about the shaft, the controller commanding different phases of the electromagnet assembly to generate the corrective force so that a vector of the corrective force rotates about the longitudinal axis of the shaft.

公开(公告)号：US11674548B2

公开(公告)日：2023-06-13

申请号：US16913019

申请日：2020-06-26

Applicant: Raytheon Technologies Corporation

Inventor： Todd A. Davis ,  Paul R. Hanrahan

IPC: F16C27/04 ,  F01D25/16 ,  F16C35/077

CPC classification number: F16C27/04 ,  F01D25/164 ,  F16C35/077 ,  F16C2360/23

Abstract: A bearing assembly of a gas turbine engine includes a bearing inner race, a bearing outer race located radially outboard of the bearing inner race and a plurality of bearing elements located between the bearing inner race and the bearing outer race. A centering spring is operably connected to and supports the bearing outer race. The centering spring is an annular structure including a base portion, a tip portion, and a plurality of beams extending axially between the base portion and the tip portion.

公开(公告)号：US20190048933A1

公开(公告)日：2019-02-14

申请号：US16078243

申请日：2016-03-01

Applicant: MITSUBISHI HEAVY INDUSTRIES ENGINE & TURBOCHARGER, LTD.

Inventor： Yuya KOJIMA ,  Tatsuya ISHIZAKI ,  Yosuke DAMMOTO ,  Yoji AKIYAMA

IPC: F16C33/10

CPC classification number: F16C33/1045 ,  F01D25/164 ,  F01D25/166 ,  F01D25/186 ,  F01M1/18 ,  F01M2011/0033 ,  F01M2011/021 ,  F05D2220/40 ,  F05D2250/15 ,  F05D2250/73 ,  F05D2260/609 ,  F16C17/02 ,  F16C17/18 ,  F16C17/26 ,  F16C33/106 ,  F16C2360/24

Abstract: The present invention improves the drainability of lubricating oil. The present invention comprises: a rotating shaft (14); a journal bearing that is provided to the rotating shaft (14) and rotationally supports the rotating shaft (14); a bearing housing part that houses the journal bearing; and a drain oil space chamber (47) that acts as an oil drainage passage that communicates with the bearing housing part, is provided along the periphery of the rotating shaft (14), and is formed to open downward. Within a region that is in and above a horizontal plane H that passes through the center of the rotating shaft (14), the smallest cross-sectional area of the oil drainage passage in a radial-direction cross-section thereof is on the anterior side in the rotational direction of the rotating shaft (14) with respect to a vertical plane P that passes though the center (O) of the rotating shaft (14), and the largest cross-sectional area of the oil drainage passage in the radial-direction cross-section is on the posterior side in the rotational direction of the rotating shaft (14) with respect to the vertical plane that passes through the center (O) of the rotating shaft (14).

公开(公告)号：US20180328225A1

公开(公告)日：2018-11-15

申请号：US15592790

申请日：2017-05-11

Applicant: United Technologies Corporation

Inventor： Todd A. Davis ,  Denman H. James ,  Daniel L. Gysling ,  Joseph D. Walker

IPC: F01D25/16 ,  F16K15/00 ,  F16C27/04 ,  F01D25/20 ,  F02C7/06

CPC classification number: F01D25/164 ,  F01D25/20 ,  F02C7/06 ,  F05D2220/32 ,  F05D2240/50 ,  F05D2240/53 ,  F05D2260/96 ,  F05D2260/98 ,  F16C27/045 ,  F16C2360/23 ,  F16F15/0237 ,  F16K15/00

Abstract: A fluid damping structure is provided that includes a damper ring. The damper ring includes an annular body a plurality of fluid check valves, and at least one fluid stop. The annular body extends circumferentially around an axial centerline, and is defined by a first end surface, a second end surface, an outer radial surface, and an inner radial surface. The outer radial surface and the inner radial surface extend axially from the first end surface toward the second end surface. The body includes one or more check valve passages. Each check valve passage extends axially from an open end disposed at the first end surface inwardly toward the second end surface, and is disposed between the inner radial surface and the outer radial surface. An inlet aperture extends between each check valve passage and the outer radial surface, and an outlet aperture extends between each check valve passage and the inner radial surface. Each fluid check valve is disposed in a check valve passage. The at least one fluid stop is configured to prevent fluid exit from the open end of each check valve passage.

公开(公告)号：US20180245632A1

公开(公告)日：2018-08-30

申请号：US15898934

申请日：2018-02-19

Applicant: HONDA MOTOR CO., LTD.

Inventor： Shinichi Obara ,  Atsushi Yamazaki

IPC: F16C27/04 ,  F16F15/023 ,  F16C33/66

CPC classification number: F16C27/045 ,  F01D25/164 ,  F01D25/20 ,  F05D2240/54 ,  F05D2260/96 ,  F05D2270/304 ,  F16C33/667 ,  F16C2360/23 ,  F16F15/0237

Abstract: A squeeze film damper bearing device includes an inner race that is fitted around an outer periphery of a rotating shaft, an outer race that is supported on an inner periphery of a bearing retaining member via an annular space, a plurality of rolling bodies that are disposed between the inner race and the outer race, and an oil supply source that supplies oil to the annular space via an oil passage so as to form a squeeze film. The device further includes an open/close valve that opens and closes the oil passage. When a rotational speed of the rotating shaft reaches a predetermined rotational speed, the open/close valve is controlled so as to change oil pressure of the squeeze film, thus changing vibration characteristics of the rotating shaft.

公开(公告)号：US20180149162A1

公开(公告)日：2018-05-31

申请号：US15363472

申请日：2016-11-29

Applicant: United Technologies Corporation

Inventor： Allison Clark Nicklous ,  Steven Tyler Englerth

IPC: F04D27/00 ,  F04D29/32 ,  F04D29/38 ,  F02K3/06 ,  F04D29/52 ,  G01L19/06

CPC classification number: F04D27/001 ,  F01D17/02 ,  F01D25/04 ,  F01D25/164 ,  F02C7/045 ,  F02C9/24 ,  F02K3/06 ,  F04D29/329 ,  F04D29/38 ,  F04D29/522 ,  F05D2260/12 ,  F05D2260/16 ,  F05D2260/80 ,  F05D2260/83 ,  F05D2260/96 ,  F05D2270/334 ,  F05D2270/804 ,  G01H1/006 ,  G01L19/0609 ,  G01M15/12

Abstract: An aero damping measurement system is provided. The system includes a shroud defining a tunnel, a hub disposed within the tunnel, and a plurality of blades coupled to the hub. The blades may rotate about the hub. A gas pressure probe may have a tip extending to the tunnel to deliver a pressurized burst into the tunnel. An aeromechanical identification system may include a pressurized gas source, a valve in fluid communication with the pressurized gas source, and the gas pressure probe may be in fluid communication with the valve. The valve may control a flow of a pressurized gas from the pressurized gas source into the gas pressure probe. A pressure sensor may be coupled to the gas pressure probe and configured to measure a pressure within the gas pressure probe.