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公开(公告)号：US20240110515A1
公开(公告)日：2024-04-04
申请号：US18071722
申请日：2022-11-30
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Andrew Hudecki , Steven Douglas Johnson , Eric Barre , John Carl Glessner , Efren Souza Chavez
CPC classification number: F02C7/18 , F01D25/12 , F05D2220/323 , F05D2260/232
Abstract: A gas turbine engine including: a fan assembly comprising a fan; and a turbomachine drivingly coupled to the fan and including a compressor section, a combustion section, and a turbine section arranged in serial flow order and defining in part a working gas flowpath, the gas turbine engine defining a bypass passage over the turbomachine; the turbomachine further including a heat exchanger and defining an annular cooling passage extending between an inlet and an outlet, the inlet in airflow communication with the working gas flowpath at a location upstream of the compressor section and the outlet in airflow communication with the bypass passage, the heat exchanger in thermal communication with an airflow through the cooling passage.
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公开(公告)号：US11788469B2
公开(公告)日：2023-10-17
申请号：US17098998
申请日：2020-11-16
Applicant: General Electric Company
Inventor： Steven Douglas Johnson , Jonathan Russell Ratzlaff
CPC classification number: F02C7/18 , F02C7/14 , B64D2033/0233 , F01D25/12 , F02C6/08 , F02C7/185 , F02C9/18 , F05D2260/20 , F05D2260/213
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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公开(公告)号：US11732592B2
公开(公告)日：2023-08-22
申请号：US17409106
申请日：2021-08-23
Applicant: General Electric Company
Inventor： Steven Douglas Johnson
CPC classification number: F01D5/187 , F01D5/081 , F05D2240/304 , F05D2260/213 , F05D2260/232 , F05D2260/601
Abstract: A gas turbine engine defining an axial direction and a radial direction, and including a primary cooling circuit configured to receive a first flow of air; and a turbine rotor comprising a rotor blade, the rotor blade defining at least in part a forward wheelspace that is located forward of the rotor blade, the forward wheelspace configured to receive a second flow of air, the rotor blade further defining: a first cooling circuit internal to the rotor blade and in fluid communication with the primary cooling circuit for receiving the first flow of air from the primary cooling circuit; a second cooling circuit internal to the rotor blade and in fluid communication with the forward wheelspace for receiving a portion of the second flow of air from the forward wheelspace; and a means for drawing a portion of the second flow of air into the second cooling circuit.
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公开(公告)号：US11692448B1
公开(公告)日：2023-07-04
申请号：US17686871
申请日：2022-03-04
Applicant: General Electric Company
Inventor： Paul Hadley Vitt , Steven Douglas Johnson
CPC classification number: F01D9/04 , F01D5/18 , F01D9/06 , F01D11/18 , F02C3/00 , F02C7/18 , Y10T137/7737
Abstract: A nozzle assembly for a gas turbine engine includes a nozzle having a first material defining a first coefficient of thermal expansion, the nozzle having an airfoil defining a fluid passage therein, an inlet wall defining a fluid inlet that is fluidly connected to the fluid passage, and a passive valve assembly comprising an annular band, the annular band comprising a second material having a second coefficient of thermal expansion less than the first coefficient of thermal expansion such that the passive valve assembly is at least partially moveable relative to the fluid inlet.
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公开(公告)号：US20230060175A1
公开(公告)日：2023-03-02
申请号：US17461142
申请日：2021-08-30
Applicant: General Electric Company
Inventor： Steven Douglas Johnson , Neelesh Nandkumar Sarawate
IPC: F01D11/12
Abstract: An abradable insert for a gas turbine engine, the abradable insert including: a base layer; a lattice layer connected to the base layer, wherein the lattice layer comprises a series of walls that define a plurality of cells; and a sheet layer connected to the lattice layer on an opposite side on the lattice layer from the base layer, wherein the sheet layer is curved and includes a direction of concavity that points away from the base layer, wherein the lattice layer and the sheet layer are integrally formed together and are a monolithic piece of material.
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Patent Agency Ranking
公开(公告)号：US20220389825A1
公开(公告)日：2022-12-08
申请号：US17338807
申请日：2021-06-04
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Steven Douglas Johnson , Kevin Randall McManus , Rahul Anil Bidkar
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.
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公开(公告)号：US11492972B2
公开(公告)日：2022-11-08
申请号：US16730570
申请日：2019-12-30
Applicant: General Electric Company
Inventor： Craig Alan Gonyou , Robert Proctor , Christopher Michael Thompson , Scott Alan Schimmels , Steven Douglas Johnson
Abstract: An annular fluid flow control or metering device comprises: first and second annular plates disposed in an annular flow path, the first annular plate and second annular plates being made of different first and second materials, the first annular plate having a lower first coefficient of thermal expansion than a second coefficient of thermal expansion of the second annular plate, the first annular plate abutting or in contact with the second annular plate, the first annular plate including at least one first metering aperture, and the second annular plate being more thermally responsive than the first annular plate wherein the second annular plate being configured to radially grow and shrink to at least partly obstruct the at least one first metering aperture for metering or controlling a flow of fluid through the at least one first metering aperture.
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公开(公告)号：US20210310422A1
公开(公告)日：2021-10-07
申请号：US17350270
申请日：2021-06-17
Applicant: General Electric Company
Inventor： Steven Douglas Johnson , Jeffrey Rambo
Abstract: A gas turbine engine includes: a compressor, a combustor, and a turbine arranged in sequential flow relationship along a primary flowpath, the turbine being connected in mechanical driving relationship to the compressor, so as to define at least one engine rotor that is rotatable about a centerline axis of the engine; a secondary flowpath connected in flow communication with the primary flowpath; and an air cycle machine including an air cycle rotor carrying an at least one air cycle compressor and at least one air cycle expander, wherein: the air cycle rotor is coupled in mechanical driving relationship with the at least one engine rotor; the air cycle rotor is coupled in fluid flow communication with the secondary flowpath; and the air cycle rotor is coupled in fluid flow communication with at least one heat exchanger.
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公开(公告)号：US10895324B2
公开(公告)日：2021-01-19
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
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.
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公开(公告)号：US10774874B2
公开(公告)日：2020-09-15
申请号：US16055333
申请日：2018-08-06
Applicant: General Electric Company
Inventor： Sean Christopher Binion , Steven Douglas Johnson , David Vickery Parker , Stephen Joseph Waymeyer , Nathan Evan McCurdy Gibson
IPC: F16C32/06 , F01D25/16 , F01D25/22 , F02C7/06 , F16C17/12 , F16C33/10 , F16C29/02 , F01D25/18 , F16C37/00
Abstract: A bearing assembly including a body defining an outer surface, an inner surface, and an aft surface is generally provided. A first inlet opening is defined through the outer surface in fluid communication with a first internal passage defined by a first internal wall. The first internal passage is in fluid communication with a first outlet opening defined through the inner surface. A second inlet opening is defined through the inner surface in fluid communication with a second internal passage defined by a second internal wall. The second internal passage is in fluid communication with a second outlet opening defined through the aft surface.
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