公开(公告)号：US20240352889A1

公开(公告)日：2024-10-24

申请号：US18137869

申请日：2023-04-21

申请人： Raytheon Technologies Corporation

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

IPC分类号： F02C7/06 ,  F16C32/04

CPC分类号： F02C7/06 ,  F01D25/162 ,  F16C32/0459 ,  F16C32/048 ,  F05D2240/515 ,  F05D2250/36 ,  F16C2360/23

摘要： A turbine engine is provided that includes a compressor section, a combustor section, a turbine section, a flowpath, a first rotating structure, a second rotating structure and a bearing system. The flowpath extends through the compressor section, the combustor section and the turbine section from an inlet to an exhaust. The combustor section includes a combustor. The first rotating structure includes a first compressor rotor within the compressor section and a first turbine rotor within the turbine section. The second rotating structure includes a second turbine rotor within the turbine section. The first turbine rotor is between the combustor and the second turbine rotor along the flowpath. The bearing system rotatably supports the first rotating structure. The bearing system includes an active magnetic bearing and a foil bearing.

公开(公告)号：US12084981B2

公开(公告)日：2024-09-10

申请号：US17656975

申请日：2022-03-29

申请人： PRATT & WHITNEY CANADA CORP.

发明人： Julien Simard-Bergeron

IPC分类号： F01D25/16 ,  F01D25/18 ,  F02B39/14 ,  F02C6/12 ,  F04D29/046 ,  F16C17/02 ,  F16C17/18 ,  F16C17/24

CPC分类号： F01D25/162 ,  F01D25/18 ,  F02B39/14 ,  F02C6/12 ,  F04D29/046 ,  F16C17/02 ,  F16C17/18 ,  F16C17/24 ,  F05D2220/40 ,  F05D2240/50 ,  F05D2260/98 ,  F16C2360/24

摘要： A journal shaft for a journal bearing assembly of an aircraft engine includes a shaft body extending along a longitudinal axis. The shaft body has a radially outer surface and a radially inner surface radially spaced apart from the longitudinal axis to define an inner cavity. An oil pocket is defined in the radially outer surface. One or more passages extend through the shaft body from the radially inner surface to the oil pocket to provide fluid communication between the inner cavity and the oil pocket. The oil pocket includes a radially inner base surface and interconnecting transition surfaces extending between the radially inner base surface of the oil pocket and the radially outer surface of the shaft body. The interconnecting transition surfaces form a fluid-dynamically smooth and edgeless transition to the radially outer surface of the journal shaft.

公开(公告)号：US12055057B2

公开(公告)日：2024-08-06

申请号：US18091517

申请日：2022-12-30

申请人： Pratt & Whitney Canada Corp.

发明人： Hien Duong ,  Vijay Kandasamy

IPC分类号： F04D29/68 ,  B64C21/02 ,  F01D5/14 ,  F01D9/02 ,  F01D25/16 ,  F04D29/32

CPC分类号： F01D25/162 ,  B64C21/02 ,  B64C21/025 ,  F01D5/145 ,  F01D9/02 ,  F04D29/682 ,  F04D29/684 ,  B64C2230/06 ,  B64C2230/20 ,  F04D29/324

摘要： A strut includes a strut body extending in a radial direction and defining an airfoil shape in cross-section perpendicular to the radial direction. The airfoil shape includes a leading edge and a trailing edge. An extraction inlet is defined through an exterior surface of the strut body, in fluid communication with an internal conduit of the strut body. An injection outlet is defined through the exterior surface of the strut body, in fluid communication with the internal conduit for fluid communication through the internal conduit from the extraction inlet to the injection outlet.

公开(公告)号：US12017962B2

公开(公告)日：2024-06-25

申请号：US16807864

申请日：2020-03-03

申请人： General Electric Company

发明人： Daniel Gene Dunn ,  Gregory Scot Corman ,  Jared Hogg Weaver

IPC分类号： F01D5/28 ,  B32B18/00 ,  C04B35/573 ,  C04B35/63 ,  C04B35/80 ,  C04B37/00 ,  C23C16/32 ,  F01D5/00 ,  F01D9/04 ,  F01D25/16 ,  F02K1/82 ,  F02K9/97 ,  F23R3/00

CPC分类号： C04B37/005 ,  B32B18/00 ,  C04B35/573 ,  C04B35/6316 ,  C04B35/80 ,  C04B37/001 ,  C23C16/325 ,  F01D5/005 ,  F01D5/282 ,  F01D5/284 ,  F01D5/288 ,  F01D9/041 ,  F01D25/162 ,  F02K1/82 ,  F02K9/97 ,  F23R3/007 ,  C04B2235/428 ,  C04B2235/5244 ,  C04B2235/616 ,  C04B2237/083 ,  C04B2237/365 ,  C04B2237/38 ,  F05D2220/32 ,  F05D2230/80 ,  F05D2240/11 ,  F05D2300/2261 ,  F05D2300/6033

摘要： Provided is a method including obtaining ceramic matrix composite (CMC) with a first matrix portion including a silicon carbide and silicon phase dispersed therewithin, disposing a coating thereupon to form a sealed part, and forming thereupon another segment comprising a CMC, which may be another matrix portion including a silicon carbide and a silicon phase dispersed within therewithin. Also provided is a gas turbine component with a CMC segment including a matrix portion including a silicon carbide and a silicon phase dispersed therewithin, a sealing layer including silicon carbide enclosing the first segment, and a second segment on the sealing layer, wherein the second segment includes a melt-infiltrated CMC having a matrix portion including a silicon carbide and a silicon phase dispersed therewithin.

公开(公告)号：US12000339B2

公开(公告)日：2024-06-04

申请号：US17526340

申请日：2021-11-15

申请人： GENERAL ELECTRIC COMPANY

发明人： Joshua Tyler Mook ,  John Alan Manteiga ,  Christopher Williams

IPC分类号： F02C7/06 ,  F01D25/16 ,  F01D25/24 ,  F02C3/14 ,  F02C7/18 ,  F02C7/20 ,  F04D29/053 ,  F04D29/056 ,  F04D29/32 ,  F04D29/54

CPC分类号： F02C7/06 ,  F01D25/162 ,  F01D25/246 ,  F02C3/14 ,  F02C7/18 ,  F02C7/20 ,  F04D29/053 ,  F04D29/056 ,  F04D29/321 ,  F04D29/541 ,  F05D2220/32 ,  F05D2240/35

摘要： The present disclosure generally relates to monolithic superstructures for supporting a rotating shaft coupled to a rotor relative to a stator. An integral superstructure supports the rotating component. The superstructure includes a bearing portion that contacts the shaft. A stator portion, is spaced a critical dimension radially outward, from the rotor. A first annular transfer portion extends axially forward from the bearing to the stator portion. A second annular transfer portion extends axially aft from the stator portion to a mounting flange. The mounting flange connects the superstructure to a frame. The superstructure maintains a critical dimension between the rotor and the stator as the temperature of the superstructure increases. The rotor may be a compressor impeller in a gas turbine engine and the stator may be an aero component that transfers air into a combustor.

公开(公告)号：US20240151182A1

公开(公告)日：2024-05-09

申请号：US18549796

申请日：2022-03-08

申请人： SAFRAN AIRCRAFT ENGINES

发明人： Paul Ghislain Albert LEVISSE ,  Emmanuel Fabrice Marie BARET ,  Julien Fabien Patrick BECOULET ,  Alexandre Jean-Marie TAN-KIM

IPC分类号： F02C7/06 ,  F01D25/16

CPC分类号： F02C7/06 ,  F01D25/162 ,  F05D2240/50 ,  F05D2260/96

摘要： A device for centering and guiding a shaft of an aircraft turbine engine, the device including an outer ring of a rolling bearing, the ring extending about an axis; an annular bearing support extending about the axis and at least partially about the ring; at least one series of connecting elements for linking the ring to the support, the connecting elements being interposed between an inner cylindrical rim of the ring and an outer cylindrical rim of the support that extends about the inner rim, and each having a first radially outer end for linking to the outer cylindrical rim and a second radially inner end for linking to the inner cylindrical rim, the ring, the support and the connecting elements being integrally formed, the connecting elements being enclosed in an annular housing that is radially delimited by the rims and laterally enclosed by an annular web.

公开(公告)号：US20240151157A1

公开(公告)日：2024-05-09

申请号：US18280806

申请日：2022-02-03

申请人： ORMAT TECHNOLOGIES, INC.

发明人： Alex KATZ ,  Yossi SIMAN TOV ,  Oren RAM

IPC分类号： F01D25/16 ,  F01D11/00

CPC分类号： F01D25/162 ,  F01D11/001

摘要： Turbine apparatus includes turbine wheels by which introduced motive fluid is expanded; a horizontally disposed turbine shaft which is rotatably supported by inlet-side and outlet-side bearings, such that the turbine wheels are fixedly connected to the turbine shaft between the inlet-side and outlet-side bearings; a turbine housing by which the turbine wheels and the outlet-side bearing are encased; and a bearing cartridge in which the inlet-side bearing is housed that is mounted externally to the turbine housing. The bearing cartridge is separable from the turbine housing to facilitate a maintenance operation when the inlet-side bearing is disengaged from the turbine shaft. In a method for accessing a malfunctioning inlet-side component contactable with the turbine shaft in order to perform a maintenance operation, the bearing cartridge is dismounted from a surface of the turbine housing and the bearing cartridge is axially displaced in a direction away from the turbine housing.

公开(公告)号：US11891909B2

公开(公告)日：2024-02-06

申请号：US18159467

申请日：2023-01-25

申请人： Transportation IP Holdings, LLC

发明人： Adam Felton ,  Christopher Homison ,  Louis Kobielski

IPC分类号： F01D25/18 ,  F01D25/16 ,  F01D15/10

CPC分类号： F01D25/18 ,  F01D15/10 ,  F01D25/162 ,  F05D2220/40 ,  F05D2240/52 ,  F05D2260/602 ,  F05D2260/98

摘要： Methods and systems are provided for electric turbochargers. In one example, a turbocharger comprises a shaft coupling a compressor wheel to a turbine wheel, an electric machine including a stator encircling the shaft between the compressor wheel and the turbine wheel, and an oil supply passage formed in a housing of the electric machine and fluidly coupled to a first oil nozzle oriented toward the shaft.

公开(公告)号：US11891905B2

公开(公告)日：2024-02-06

申请号：US17644475

申请日：2021-12-15

申请人： General Electric Company

发明人： Prashant Bhujabal ,  Ravindra Shankar Ganiger ,  Narayanan Payyoor ,  Mohankumar Banakar ,  Weize Kang

IPC分类号： F01D25/16 ,  F01D5/06 ,  F02C7/06

CPC分类号： F01D25/162 ,  F01D5/06 ,  F02C7/06 ,  F05D2240/54 ,  F05D2240/61 ,  F05D2260/40311

摘要： A bearing support assembly to support one or more bearings on a shaft. The bearing support assembly includes a bearing support frame configured to be coupled to a static frame, a plurality of ribs connected to the bearing support frame, and a bearing support connected to the plurality of ribs and configured to support a bearing of the one or more bearings. The bearing support assembly has a non-axisymmetric stiffness around a circumference of the bearing support assembly.

公开(公告)号：US20240011415A1

公开(公告)日：2024-01-11

申请号：US17858293

申请日：2022-07-06

申请人： PRATT & WHITNEY CANADA CORP.

发明人： Guy LEFEBVRE ,  Remy SYNNOTT

IPC分类号： F01D25/16

CPC分类号： F01D25/162 ,  F05D2220/323 ,  F05D2260/96 ,  F05D2260/39 ,  F01D9/026

摘要： The damper segment can be assembled between adjacent segments of a pressurized gas pipe of an aircraft engine. The damper segment can have a proximal end, a distal end, a rigid tube at the proximal end, a damper tube extending between the rigid tube and the distal end, the damper tube being made of a metal mesh, a proximal catch structurally connecting a proximal end of the damper tube to the rigid tube, and a distal catch structurally connected between a distal end of the damper tube and the distal end, the damper tube having an unsupported length extending between the distal catch and the proximal catch, the rigid tube having a liner portion projecting into the distal segment, the liner portion extending internally relative the damper tube.