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公开(公告)号：US20180209299A1
公开(公告)日：2018-07-26
申请号：US15411549
申请日：2017-01-20
Applicant: General Electric Company
Inventor： Steven Douglas Johnson , Nicholas R. Dinsmore , Daniel Tyler Jarboe
CPC classification number: F01D25/12 , F01D9/041 , F01D9/065 , F01D11/001 , F01D11/02 , F01D11/06 , F05D2220/32 , F05D2240/55 , F05D2260/20 , F05D2260/60
Abstract: A gas turbine engine that includes a turbine interstage region. The turbine interstage region is configured to conduct bore bleed air outwardly. The interstage region includes a central plenum. The interstage region also includes a first mid-seal and a second mid-seal. The central plenum is fluidly connected to bore bleed air by a flow circuit that passes between the first mid-seal and the second mid-seal.
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公开(公告)号：US20240263883A1
公开(公告)日：2024-08-08
申请号：US18613306
申请日：2024-03-22
Applicant: General Electric Company
Inventor： Nicholas M. Daggett , Steven Douglas Johnson , Anand P. Roday , Scott Alan Schimmels
CPC classification number: F28D1/0443 , F28D1/0233 , F28D1/0475 , F28F9/001 , F28D2001/0273
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.
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公开(公告)号：US11988096B2
公开(公告)日：2024-05-21
申请号：US17841847
申请日：2022-06-16
Inventor： Ravindra Shankar Ganiger , Neelesh Nandkumar Sarawate , Rahul Anil Bidkar , Narendra Anand Hardikar , Kevin Randall McManus , Steven Douglas Johnson , Prateek Jalan , Antonio Guijarro Valencia , Julius John Montgomery , Rodrigo Rodriguez Erdmenger , Jose Maria Rey Villazon
CPC classification number: F01D11/003 , F01D11/001 , F01D11/02 , F05D2220/323 , F05D2240/56
Abstract: A seal assembly for a rotary machine, such as a turbine engine, may include a seal rotor comprising a rotor face, a seal slider comprising a slider face, a seal stator, wherein the seal slider is slidably coupled to the seal stator, and wherein the slider face and the rotor face define a primary seal. The seal slider may be configured to slidably engage and retract the slider face with respect to the rotor face. The seal assembly may further include a secondary seal disposed between the seal slider and the seal stator. The secondary seal may be configured to compress and rebound and/or to expand and rebound, over at least a portion of a range of motion of the seal slider.
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公开(公告)号：US11976562B2
公开(公告)日：2024-05-07
申请号：US18297835
申请日：2023-04-10
Applicant: General Electric Company
Inventor： Steven Douglas Johnson , Julius John Montgomery , Brandon Wayne Miller , Robert Proctor , Bradley W. Fintel , Jeffrey Douglas Rambo
CPC classification number: F01D11/24 , F01D5/03 , F01D11/18 , F02C6/08 , F02C7/185 , F01D25/12 , F01D25/14 , F05D2220/323 , F05D2240/11 , F05D2240/55 , F05D2260/20 , F05D2260/30
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.
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公开(公告)号：US20230417188A1
公开(公告)日：2023-12-28
申请号：US18462587
申请日：2023-09-07
Applicant: General Electric Company
Inventor： Steven Douglas Johnson , Jonathan Russell Ratzlaff
CPC classification number: F02C7/18 , F02C7/14 , F05D2260/20 , F01D25/12
Abstract: A thermal management system for a gas turbine engine includes a heat exchanger including first and second sides, with the first side in contact with flow path air flowing through a flow path of the engine. Furthermore, the system includes a housing positioned relative to the heat exchanger such that the housing and the second side of the heat exchanger define a plenum configured to receive bleed air from the engine. Moreover, the system includes and at least one of a plurality of fins extending outward from the second side of the heat exchanger in a radial direction into the plenum and along the second surface of the heat exchanger in the circumferential direction or an impingement plate defining a plurality of impingement apertures, with each impingement aperture configured to direct an impingement jet of the bleed air within the plenum onto the second side of the heat exchanger.
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Patent Agency Ranking
公开(公告)号：US20230279781A1
公开(公告)日：2023-09-07
申请号：US17841847
申请日：2022-06-16
Inventor： Ravindra Shankar Ganiger , Neelesh Nandkumar Sarawate , Rahul Anil Bidkar , Narendra Anand Hardikar , Kevin Randall McManus , Steven Douglas Johnson , Prateek Jalan , Antonio Guijarro Valencia , Julius John Montgomery , Rodrigo Rodriguez Erdmenger , Jose Maria Rey Villazon
CPC classification number: F01D11/003 , F01D11/02 , F01D11/001 , F05D2240/56 , F05D2220/323
Abstract: A seal assembly for a rotary machine, such as a turbine engine, may include a seal rotor comprising a rotor face, a seal slider comprising a slider face, a seal stator, wherein the seal slider is slidably coupled to the seal stator, and wherein the slider face and the rotor face define a primary seal. The seal slider may be configured to slidably engage and retract the slider face with respect to the rotor face. The seal assembly may further include a secondary seal disposed between the seal slider and the seal stator. The secondary seal may be configured to compress and rebound and/or to expand and rebound, over at least a portion of a range of motion of the seal slider.
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公开(公告)号：US20220282670A1
公开(公告)日：2022-09-08
申请号：US17190076
申请日：2021-03-02
Applicant: General Electric Company
Inventor： Daniel Alan Niergarth , Nicholas M. Daggett , Steven Douglas Johnson , Anand P. Roday , Scott Alan Schimmels
Abstract: A three-stream engine is provided. The three-stream engine includes a fan section, a core engine disposed downstream of the fan section, and a core cowl annularly encasing the core engine and at least partially defining a core duct. A fan cowl is disposed radially outward from the core cowl and annularly encasing at least a portion of the core cowl. The fan cowl at least partially defining an inlet duct and a fan duct. The fan duct and the core duct at least partially co-extending axially on opposite sides of the core cowl. A heat exchanger disposed within the fan duct. The heat exchanger provides for thermal communication between a fluid flowing through fan duct and a motive fluid flowing through the heat exchanger.
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公开(公告)号：US20200157970A1
公开(公告)日：2020-05-21
申请号：US16715706
申请日：2019-12-16
Applicant: General Electric Company
Inventor： Steven Douglas Johnson , Nicholas R. Dinsmore , Daniel Tyler Jarboe
Abstract: A gas turbine engine that includes a turbine interstage region. The turbine interstage region is configured to conduct bore bleed air outwardly. The interstage region includes a central plenum. The interstage region also includes a first mid-seal and a second mid-seal. The central plenum is fluidly connected to bore bleed air by a flow circuit that passes between the first mid-seal and the second mid-seal.
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公开(公告)号：US10544702B2
公开(公告)日：2020-01-28
申请号：US15411549
申请日：2017-01-20
Applicant: General Electric Company
Inventor： Steven Douglas Johnson , Nicholas R. Dinsmore , Daniel Tyler Jarboe
Abstract: A gas turbine engine that includes a turbine interstage region. The turbine interstage region is configured to conduct bore bleed air outwardly. The interstage region includes a central plenum. The interstage region also includes a first mid-seal and a second mid-seal. The central plenum is fluidly connected to bore bleed air by a flow circuit that passes between the first mid-seal and the second mid-seal.
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公开(公告)号：US20190203842A1
公开(公告)日：2019-07-04
申请号：US16296620
申请日：2019-03-08
Applicant: General Electric Company
IPC: F16J15/447 , F01D11/02 , F01D11/08
CPC classification number: F16J15/4476 , F01D11/02 , F01D11/08
Abstract: A seal assembly of a rotary includes a radially oriented plate that axially opposes a front and rear support plates of a stator interface. The seal assembly also includes a film-riding shoe coupled with the radially oriented plate. The shoe forms a shoe fluid bearing between the shoe and a rotating component responsive to rotation of the rotating component and pressurization of fluid in the rotary machine upstream of the stator interface. One or more of the stator interface or the film-riding shoe includes one or more ports or pathways through which higher-pressure fluid upstream of the stator housing in the rotary machine flows to form an aft axial fluid bearing between the radially oriented plate and the rear support plate of the stator interface.
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