公开(公告)号：US12209511B2

公开(公告)日：2025-01-28

申请号：US17316788

申请日：2021-05-11

Applicant: BorgWarner Inc.

Inventor： Thomas Ramb ,  Bernhard Dreher ,  Patrick Weber ,  Alexander Umlauff ,  Ahmet Coksen

IPC: F01D9/04 ,  F01D25/16 ,  F01D25/24 ,  F01D25/28 ,  F02C6/12

Abstract: Disclosed is a turbine arrangement for a supercharging device. The turbine arrangement comprises a turbine housing, a turbine wheel and a guide device. The turbine housing defines a turbine spiral and a turbine outlet. The turbine wheel is arranged in the turbine housing between the turbine spiral and the turbine outlet. The guide device comprises a carrier ring and multiple guide blades. The guide blades are arranged on the carrier ring fixedly in a predetermined orientation. The guide device is arranged in an inflow channel between the turbine spiral and the turbine wheel such that, during operation, fluids are conducted from the turbine spiral through the inflow channel over the guide blades onto the turbine wheel.

公开(公告)号：US20250027423A1

公开(公告)日：2025-01-23

申请号：US18224934

申请日：2023-07-21

Applicant: Raytheon Technologies Corporation

Inventor： Andrew E. Breault ,  Jeffrey T. Morton

IPC: F01D11/14 ,  F01D25/16

Abstract: An assembly is provided for an aircraft powerplant. This assembly includes a rotating assembly, a first structure, a second structure and a thrust bearing. The rotating assembly includes a first bladed rotor and a second bladed rotor. The first bladed rotor includes a plurality of first rotor blades. The second bladed rotor includes a plurality of second rotor blades. The first structure is configured as or otherwise includes a first shroud. The first shroud circumscribes the first bladed rotor. The first shroud is adjacent first tips of the first rotor blades. The second structure is configured as or otherwise includes a second shroud. The second shroud circumscribes the second bladed rotor. The second shroud is adjacent second tips of the second rotor blades. The second shroud is configured to move along an axis relative to the first shroud. The thrust bearing couples the rotating assembly to the second structure.

公开(公告)号：US12203382B1

公开(公告)日：2025-01-21

申请号：US18382671

申请日：2023-10-23

Applicant: RTX CORPORATION

Inventor： Christopher T. Anglin ,  Kiomarys Mariel Toro

IPC: F01D25/18 ,  F01D25/16 ,  F16C33/66

Abstract: A turbine engine assembly includes a shaft rotatable about an engine axis, the shaft includes slots that are formed on an outer surface and passages between an inner cavity to the outer surface, and a bearing assembly that is configured to support rotation of the shaft. The bearing assembly includes an inner race that is supported on the outer surface of the shaft over the slots. At least one bearing member is supported in the inner race, an outer race, a first cover that is disposed on a forward side of the inner race and a second cover that is disposed on an aft side of the inner race. Each of the first cover and the second cover include radially extending grooves for communicating lubricant from the slots to the bearing member.

公开(公告)号：US12188363B2

公开(公告)日：2025-01-07

申请号：US18613901

申请日：2024-03-22

Applicant: Unison Industries, LLC ,  General Electric Company

Inventor： Amit Arvind Kurvinkop ,  David Raju Yamarthi ,  David Allan Dranschak ,  Brian Christopher Kemp ,  Marc David Zinger ,  Parmeet Singh Chhabra ,  Roberto Karpik ,  Eliel Fresco Rodriguez

IPC: F01D25/16 ,  F02C7/27

Abstract: An air turbine starter that includes a housing. The housing can circumscribe a turbine coupled that is coupled to a gear train in a gear box via a drive shaft. The gear train can couple to an output shaft via at least a carrier. The air turbine starter can include at least a first bearing assembly and a second bearing assembly to rotatably support the drive shaft and the output shaft.

公开(公告)号：US20240426227A1

公开(公告)日：2024-12-26

申请号：US18340443

申请日：2023-06-23

Applicant: Pratt & Whitney Canada Corp.

Inventor： Lorenzo Sanzari ,  Guy Lefebvre

IPC: F01D25/16

Abstract: A bearing assembly for a turbomachine includes a bearing inner race, a bearing outer race located radially outwardly from the bearing inner race, and one or more bearing elements located radially between the bearing inner race and the bearing outer race. A bearing sleeve is positioned radially inboard of the bearing inner race and is configured for engagement with a rotating component. The bearing sleeve includes a sleeve body located radially between the bearing inner race and the rotating component, and a puller feature extending from the sleeve body at a first axial end of the bearing sleeve. The puller feature is configured for application of a removal force thereto to remove the bearing from an installed position in the turbomachine.

公开(公告)号：US20240401500A1

公开(公告)日：2024-12-05

申请号：US18420862

申请日：2024-01-24

Applicant: RTX CORPORATION

Inventor： Frederick M. Schwarz ,  Gabriel L. Suciu ,  William K. Ackermann ,  Daniel Bernard Kupratis ,  Michael E. McCune

IPC: F01D25/16 ,  F01D15/12 ,  F02C3/107 ,  F02C7/06 ,  F02C7/20 ,  F02C7/36 ,  F02K3/06

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, propulsor means, first compression means, second compression means, reduction means for reducing a rotational speed of an output that drives the propulsor means relative to an input, first expansion means, and second expansion means. The reduction means includes an epicyclic gear system with a gear reduction. The gear system is straddle-mounted by first and second bearings on opposite sides of the gear reduction relative to an engine longitudinal axis.

公开(公告)号：US12140080B2

公开(公告)日：2024-11-12

申请号：US17987303

申请日：2022-11-15

Applicant: Raytheon Technologies Corporation

Inventor： Gary D. Roberge

IPC: F02C7/32 ,  F01D25/16 ,  F01D25/24 ,  B33Y80/00

Abstract: A gas turbine engine includes an engine case along an engine axis, a conformal accessory drive gearbox housing mounted to the engine case, and at least one accessory mounted to the conformal housing.

公开(公告)号：US20240352969A1

公开(公告)日：2024-10-24

申请号：US18137871

申请日：2023-04-21

Applicant: Raytheon Technologies Corporation

Inventor： Alexander R. Nelson ,  Benstone I. Schwartz ,  Philip A. Varney ,  Andrew V. Schwendenmann

IPC: F16C32/04 ,  F01D25/16 ,  F16C17/02

CPC classification number: F16C32/0444 ,  F01D25/16 ,  F16C17/024 ,  F05D2240/51 ,  F16C2360/23

Abstract: An assembly is provided that includes a rotating structure, a bearing, a sensor system, a power system and a controller. The rotating structure is rotatable about an axis. The bearing rotatably supports the rotating structure. The bearing includes a magnetic bearing stator and a magnetic bearing rotor mounted with the rotating structure. The sensor system is configured to provide bearing sensor data indicative of a position of the magnetic bearing rotor relative to the magnetic bearing stator. The power system is electrically coupled to the magnetic bearing stator. The controller is configured to signal the power system to power the magnetic bearing stator based on the bearing sensor data. The controller is configured to monitor health of the rotating structure based on the bearing sensor data.

公开(公告)号：US20240352864A1

公开(公告)日：2024-10-24

申请号：US18357301

申请日：2023-07-24

Applicant: General Electric Company

Inventor： Narendra Anand Hardikar ,  David Raju Yamarthi ,  Ravindra Shankar Ganiger ,  Mohan Kannaiah Raju

IPC: F01D11/08 ,  F01D25/16

CPC classification number: F01D11/08 ,  F01D25/16 ,  F05D2220/32 ,  F05D2240/50 ,  F05D2240/55

Abstract: A turbine engine includes a rotor, a stator having a carrier, and a seal assembly that is disposed between the rotor and the stator. The seal assembly includes a plurality of seal segments. The plurality of seal segments includes a seal segment having a seal face forming a fluid bearing with the rotor, a body, and an aft bearing extending from the body. The turbine engine further includes a roller assembly having one or more rolling elements coupled to one of the aft bearing or the carrier. The one or more rolling elements in rolling contact with the other of the aft bearing or the carrier.

公开(公告)号：US12116901B2

公开(公告)日：2024-10-15

申请号：US18260978

申请日：2022-01-10

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Julien Fabien Patrick Becoulet ,  Olivier Formica

IPC: F01D25/18 ,  F01D25/16 ,  F02C3/107 ,  F02C7/06 ,  F02C7/28

CPC classification number: F01D25/183 ,  F01D25/16 ,  F02C3/107 ,  F02C7/06 ,  F02C7/28 ,  F05D2220/32 ,  F05D2240/50 ,  F05D2240/55 ,  F05D2240/60 ,  F05D2260/40 ,  F05D2260/98

Abstract: A turbomachine fan module includes a fan shaft and a lubrication chamber traversed axially by at least part of the fan shaft. The module further includes at least one first bearing configured to support and guide the fan shaft in rotation. The fan shaft has a first tubular part closed by a cover, wherein the first tubular part has a distal end and a proximal end that are opposite each other along a longitudinal axis X and an annular squealer cavity, formed in an inner surface of the fan shaft, between the distal end and the proximal end. The cover has a body extending along the longitudinal axis X and mounted in the first tubular portion so as to cover and sealingly close the annular squealer cavity.