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公开(公告)号：US20230228214A1
公开(公告)日：2023-07-20
申请号：US17578795
申请日：2022-01-19
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Scott David Hunter , Patrick Michael Marrinan , Scott Alan Schimmels
CPC classification number: F02K3/04 , F02C9/00 , F05D2220/76 , F05D2220/32
Abstract: A gas turbine engine includes a turbomachine, the turbomachine defining a core flow therethrough during operation. A first heat exchange assembly is in fluid communication with the turbomachine for receiving a first bleed flow from the turbomachine. A second heat exchange assembly is in fluid communication with the turbomachine for receiving a second bleed flow from the turbomachine. A first flow outlet is provided for receiving the first bleed flow from the first heat exchange assembly and providing the first bleed flow to a first aircraft flow assembly. A second flow outlet is provided for receiving the second bleed flow and providing the second bleed flow from the second heat exchange assembly to a second aircraft flow assembly.
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公开(公告)号：US12116929B2
公开(公告)日：2024-10-15
申请号：US17578795
申请日：2022-01-19
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Scott David Hunter , Patrick Michael Marrinan , Scott Alan Schimmels
CPC classification number: F02C6/08 , B64D13/06 , F02C9/00 , F02C9/18 , F02K3/04 , B64D2013/0603 , B64D2013/0607 , B64D2013/0618 , B64D2013/0648 , F05D2220/32 , F05D2220/76
Abstract: A gas turbine engine includes a turbomachine, the turbomachine defining a core flow therethrough during operation. A first heat exchange assembly is in fluid communication with the turbomachine for receiving a first bleed flow from the turbomachine. A second heat exchange assembly is in fluid communication with the turbomachine for receiving a second bleed flow from the turbomachine. A first flow outlet is provided for receiving the first bleed flow from the first heat exchange assembly and providing the first bleed flow to a first aircraft flow assembly. A second flow outlet is provided for receiving the second bleed flow and providing the second bleed flow from the second heat exchange assembly to a second aircraft flow assembly.
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公开(公告)号：US11092013B2
公开(公告)日：2021-08-17
申请号：US16236018
申请日：2018-12-28
Applicant: General Electric Company
Inventor： John Joseph Rahaim , Daniel John Fusinato , Scott David Hunter , Joel Francis Kirk , Michael Robert Melzak , Curtis Walton Stover
Abstract: A flow transfer apparatus for transferring cooling flow from a primary gas flowpath to a turbine rotor. The apparatus includes a first supply plenum communicating with the primary gas flowpath and first inducers, the first inducers configured to accelerate a first fluid flow from the first supply plenum and discharge it toward the rotor with a tangential velocity; a second supply plenum communicating with the primary gas flowpath and second inducers, the second inducers configured to accelerate a second fluid flow from the second supply plenum towards the rotor with a tangential velocity; and a cooling modulation valve operable to selectively permit or block the second fluid flow from the primary gas flowpath to the second supply plenum. The valve includes a flow control structure disposed in the primary gas flowpath and an actuation structure extending to a location radially outside of a casing defining the primary gas flowpath.
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Patent Agency Ranking
公开(公告)号：US11788465B2
公开(公告)日：2023-10-17
申请号：US17578612
申请日：2022-01-19
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Patrick Michael Marrinan , Arthur William Sibbach , Scott Alan Schimmels , Scott David Hunter
CPC classification number: F02C6/06 , F02C6/08 , F02C7/32 , F02C9/00 , F02K3/04 , F05D2220/32 , F05D2220/76
Abstract: A gas turbine engine comprises a turbomachine defining a core flow therethrough during operation. A flow tap is provided in fluid communication with the turbomachine, wherein the flow tap is configured to receive a portion of the core flow therethrough as a bleed flow. A bleed assembly includes a machine load, a bleed flow machine, and a bleed regulator. The bleed flow machine is disposed in fluid communication with the turbomachine through the flow tap, and is configured to drive the machine load. The bleed regulator is configured to regulate a bleed output provided to the bleed flow machine by controlling a capture rate of the bleed flow by the bleed flow machine.
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公开(公告)号：US20230228213A1
公开(公告)日：2023-07-20
申请号：US17578612
申请日：2022-01-19
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Patrick Michael Marrinan , Arthur William Sibbach , Scott Alan Schimmels , Scott David Hunter
CPC classification number: F02K3/04 , F02C9/00 , F05D2220/32 , F05D2220/76
Abstract: A gas turbine engine comprises a turbomachine defining a core flow therethrough during operation. A flow tap is provided in fluid communication with the turbomachine, wherein the flow tap is configured to receive a portion of the core flow therethrough as a bleed flow. A bleed assembly includes a machine load, a bleed flow machine, and a bleed regulator. The bleed flow machine is disposed in fluid communication with the turbomachine through the flow tap, and is configured to drive the machine load. The bleed regulator is configured to regulate a bleed output provided to the bleed flow machine by controlling a capture rate of the bleed flow by the bleed flow machine.
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公开(公告)号：US20230228231A1
公开(公告)日：2023-07-20
申请号：US17578791
申请日：2022-01-19
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Scott David Hunter , Scott Alan Schimmels , Patrick Michael Marrinan
CPC classification number: F02K3/04 , F02C9/00 , F05D2220/32 , F05D2220/76
Abstract: A gas turbine engine includes a turbomachine defining a core flow therethrough during operation. A first flow tap is configured to receive a first bleed flow from upstream of the combustion section. A second flow tap is configured to receive a second bleed flow from downstream of the combustion section. A first flow outlet is provided in fluid communication with the first flow tap and a second flow outlet is provided in fluid communication with the second flow tap. The first flow outlet and the second flow outlet are configured to direct the first bleed flow and the second bleed flow to at least one aircraft flow assembly.
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公开(公告)号：US20230228216A1
公开(公告)日：2023-07-20
申请号：US17578787
申请日：2022-01-19
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Scott David Hunter , Patrick Michael Marrinan , Scott Alan Schimmels
CPC classification number: F02C7/18 , F02C6/08 , F05D2260/213
Abstract: A gas turbine engine may include a turbomachine defining a core flow having a core mass flow rate therethrough during operation. A bleed assembly is provided to include a bleed flow machine and a machine load. The bleed flow machine is provided in fluid communication with the compressor section of the turbomachine and configured to drive the machine load. A machine outlet in fluid communication with the bleed assembly provides a bleed flow therethrough during operation of the gas turbine engine, the bleed flow defining a bleed mass flow rate. A compressor section of the turbomachine is configured to provide the bleed flow through the bleed flow machine and the machine outlet to an aircraft flow assembly, wherein the bleed mass flow rate is at least twelve percent (12%) of the core mass flow rate.
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公开(公告)号：US10202867B2
公开(公告)日：2019-02-12
申请号：US14777331
申请日：2014-03-14
Applicant: General Electric Company
Inventor： John Joseph Rahaim , Daniel John Fusinato , Scott David Hunter , Joel Francis Kirk , Michael Robert Melzak , Curtis Walton Stover
Abstract: A flow transfer apparatus for transferring cooling flow from a primary gas flowpath to a turbine rotor. The apparatus includes a first supply plenum communicating with the primary gas flowpath and first inducers, the first inducers configured to accelerate a first fluid flow from the first supply plenum and discharge it toward the rotor with a tangential velocity; a second supply plenum communicating with the primary gas flowpath and second inducers, the second inducers configured to accelerate a second fluid flow from the second supply plenum towards the rotor with a tangential velocity; and a cooling modulation valve operable to selectively permit or block the second fluid flow from the primary gas flowpath to the second supply plenum. The valve includes a flow control structure disposed in the primary gas flowpath and an actuation structure extending to a location radially outside of a casing defining the primary gas flowpath.
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