公开(公告)号：US12241375B2

公开(公告)日：2025-03-04

申请号：US18189379

申请日：2023-03-24

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  David Raju Yamarthi ,  Chandrashekhar Kandukuri ,  Deepak Trivedi ,  Narendra Anand Hardikar ,  Vidyashankar Ramasastry Buravalla ,  Steven Douglas Johnson ,  Amit Goyal ,  Grant Robert Portune ,  Himanshu Gupta ,  Srinivasan Swaminathan ,  Shalini Thimmegowda ,  Guru Venkata Dattu Jonnalagadda ,  Shalabh Saxena ,  Prateek Jalan

IPC: F01D11/02

Abstract: A turbine engine is provided. The turbine engine defines an axial direction and a radial direction, and includes: a rotor; a stator comprising a carrier; a seal assembly disposed between the rotor and the stator, the seal assembly defining a high-pressure side and a low-pressure side and comprising a plurality of seal segments, the plurality of seal segments including a seal segment having a seal face forming a fluid bearing with the rotor, a lip, and a body, the lip extending from the body along the axial direction of the turbine engine on the high-pressure side and including an outer pressurization surface along the radial direction of the turbine engine; and a seal support assembly, the seal support assembly comprising a spring arrangement extending between the carrier and the first seal segment to counter a pressure on the outer pressurization surface during operation of the turbine engine.

公开(公告)号：US20240229658A9

公开(公告)日：2024-07-11

申请号：US17970918

申请日：2022-10-21

Applicant: GENERAL ELECTRIC COMPANY ,  General Electric Deutschland Holding GmbH

Inventor： Antonio Guijarro Valencia ,  Scott Alan Schimmels ,  Steven Douglas Johnson

IPC: F01D9/04

CPC classification number: F01D9/041 ,  F05D2240/128 ,  F05D2250/323 ,  F05D2250/38 ,  F05D2260/2212 ,  F05D2260/606 ,  F05D2260/97

Abstract: A turbine engine having a rotor rotatable about a rotational axis, a stator, a plurality of circumferentially spaced bleed air passages, and an inducer. The plurality of circumferentially spaced bleed air passages being located between an axially adjacent set of vanes of the stator and blades of the rotor. The inducer including a nozzle passage fluidly coupling a nozzle inlet of the inducer to a nozzle outlet of the inducer.

公开(公告)号：US20240200463A1

公开(公告)日：2024-06-20

申请号：US18586765

申请日：2024-02-26

Applicant: General Electric Company

Inventor： Steven Douglas Johnson ,  Yu-Liang Lin ,  Craig Alan Gonyou ,  Scott Alan Schimmels ,  Jeffrey Douglas Rambo ,  Brian Gregg Feie

IPC: F01D9/06 ,  F01D5/08

CPC classification number: F01D9/06 ,  F01D5/081 ,  F05D2240/128 ,  F05D2260/232 ,  F05D2260/606

Abstract: A passive flow modulation device for a machine defining an axial direction and a radial direction, the passive flow modulation device including: a first ring with a first coefficient of thermal expansion; a second ring disposed coaxially with the first ring and positioned at least partially inward of the first ring along the radial direction, spaced from the first ring along the axial direction, or both, the first ring, the second ring, or both defining at least in part one or more passages, the second ring with a second coefficient of thermal expansion that is less than the first coefficient of thermal expansion to passively modulate a size of the one or more passages during operation.

公开(公告)号：US12000296B2

公开(公告)日：2024-06-04

申请号：US17676929

申请日：2022-02-22

Applicant: General Electric Company

Inventor： Steven Douglas Johnson ,  Neelesh Nandkumar Sarawate

IPC: F01D11/02 ,  F01D5/02 ,  F01D9/02 ,  F01D11/00 ,  F01D11/12 ,  F01D25/04

CPC classification number: F01D25/04 ,  F01D5/02 ,  F01D9/02 ,  F01D11/001 ,  F01D11/127 ,  F05D2240/56 ,  F05D2260/96

Abstract: A seal for a rotor is provided. The rotor defines an axial direction, a circumferential direction, and a radial direction. The seal includes a first flexible element coupled to the rotor. The first flexible element extends in a first direction that is within forty five degrees of the axial direction.

公开(公告)号：US11821320B2

公开(公告)日：2023-11-21

申请号：US17338807

申请日：2021-06-04

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Steven Douglas Johnson ,  Kevin Randall McManus ,  Rahul Anil Bidkar

IPC: F01D11/22 ,  F01D11/00 ,  F01D11/02

CPC classification number: F01D11/001 ,  F01D11/025 ,  F01D11/22 ,  F05D2220/323 ,  F05D2240/11 ,  F05D2240/80 ,  F05D2260/38

Abstract: A turbine engine comprising an engine core having at least a compressor section, a combustor section, and a turbine section in axial flow arrangement defining an axial direction and an engine centerline. The turbine engine further having a rotor and a stator, a carriage assembly carried by the stator, and a seal assembly biased toward the rotor.

公开(公告)号：US20230036206A1

公开(公告)日：2023-02-02

申请号：US17389503

申请日：2021-07-30

Applicant: General Electric Company

Inventor： Steven Douglas Johnson ,  Jonathan Russell Ratzlaff ,  Craig Alan Gonyou

IPC: F01D5/08 ,  F01D25/12

Abstract: A gas turbine engine includes a combustion section, a turbine section, and a compressor section. The combustion section includes a combustor casing, a combustor, a cooling duct, and an outer duct. The combustor casing defines at least in part a diffuser cavity and a fluid inlet. The combustor disposed is in the diffuser cavity. The cooling duct is in fluid communication with the fluid inlet in the combustor casing and is configured to transport a flow of cooled air. The outer duct surrounds at least a portion of the cooling duct and extends along a portion of an entire length of the cooling duct. The outer duct defines a gap with the cooling duct and is configured to transport a flow of buffer air. The turbine section is disposed downstream from the combustion section. The cooling duct is in fluid communication with the turbine section.

公开(公告)号：US20220282925A1

公开(公告)日：2022-09-08

申请号：US17190103

申请日：2021-03-02

Applicant: General Electric Company

Inventor： Nicholas M. Daggett ,  Steven Douglas Johnson ,  Anand P. Roday ,  Scott Alan Schimmels

IPC: F28D1/04 ,  F28D1/02 ,  F28F9/00 ,  F28D1/047

Abstract: A heat exchanger is provided. The heat exchanger includes a first wall manifold. The heat exchanger further includes a second wall manifold spaced apart from the first wall manifold. The heat exchanger further includes a plurality of vanes that extend generally circumferentially between the first wall manifold and the second wall manifold. The heat exchanger further includes a plurality of fluid circuits defined within the heat exchanger. Each fluid circuit in the plurality of fluid circuits includes an inlet channel portion and an outlet channel portion defined within the first wall manifold. A return channel portion defined within the second wall manifold. At least one passage portion of a plurality of passage portions defined within each vane of the plurality of vanes. The at least one passage portion extends between the return channel portion and one of the inlet channel portion and the outlet channel portion.

公开(公告)号：US20220213802A1

公开(公告)日：2022-07-07

申请号：US17142357

申请日：2021-01-06

Applicant: General Electric Company

Inventor： Steven Douglas Johnson ,  Julius John Montgomery ,  Brandon Wayne Miller ,  Robert Proctor ,  Bradley W. Fintel ,  Jeffrey Douglas Rambo

IPC: F01D11/24 ,  F01D11/18

Abstract: A system for controlling blade clearances within a gas turbine engine includes a rotor disk and a rotor blade coupled to the rotor disk. Additionally, the system includes an outer turbine component positioned outward of the rotor blade such that a clearance is defined between the rotor blade and the outer turbine component. Furthermore, the system includes a heat exchanger configured to receive a flow of cooling air bled from the gas turbine engine and transfer heat from the received flow of the cooling air to a flow of coolant to generate cooled cooling air. Moreover, the system includes a valve configured to control the flow of the coolant to the heat exchanger. In this respect, the cooled cooling air is supplied to at least one of the rotor disk or the rotor blade to adjust the clearance between the rotor blade and the outer turbine component.

公开(公告)号：US11300368B2

公开(公告)日：2022-04-12

申请号：US16532846

申请日：2019-08-06

Applicant: General Electric Company

Inventor： Thomas Kupiszewski ,  Christopher Charles Glynn ,  Steven Douglas Johnson ,  John Andrew Kemme ,  Mehdi Milani Baladi ,  Michael Epstein

IPC: F28F7/02 ,  F28F19/02 ,  F28F1/06 ,  F28F1/40 ,  F28F21/08 ,  F28F13/12 ,  F28D21/00

Abstract: A cross-flow heat exchanger for gas turbine engines which may be utilized to transfer heat from one fluid flow 46 to a second independent fluid flow wherein one of the fluid flows has a high differential inlet pressure and temperature. The heat exchanger has robust construction to inhibit mixing of the fluid flows during a single burst duct event.

公开(公告)号：US20200166143A1

公开(公告)日：2020-05-28

申请号：US16201669

申请日：2018-11-27

Applicant: General Electric Company

Inventor： Quang Tue Nguyen Tran ,  Nathan Evan McCurdy Gibson ,  Rodrigo Rodriguez Erdmenger ,  Christopher Edward Wolfe ,  Steven Douglas Johnson ,  Antonio Guijarro Valencia

IPC: F16J15/44 ,  F01D5/22 ,  F01D5/20 ,  F16J15/40

Abstract: A seal assembly for a rotary machine includes a seal bearing face that opposes a rotating component of the machine and a slide device coupled with the seal bearing face. The slide device axially moves toward the rotating component responsive to pressurization of the rotary machine. The slide device includes cross-over ports and the seal bearing includes feed ports. The feed ports extend through the seal bearing face to form aerostatic portions of a film bearing between the seal bearing face and the rotating component. The seal bearing face and/or the rotating component has a non-planar surface that, during rotating motion of the rotating component relative to the face of the seal bearing face, forms aerodynamic portions of the film bearing.