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公开(公告)号：US12173654B2
公开(公告)日：2024-12-24
申请号：US18456966
申请日：2023-08-28
Applicant: General Electric Company
Inventor： Jeffrey Douglas Rambo , Gregory Michael Petrasko
Abstract: A system for energy conversion that includes a propulsion system, a fuel circuit, a combustion device, a turbine, and a load device. The fuel circuit is in fluid communication with a fuel tank and a fuel flow control device that separates a flow of fuel into a first portion and a second portion. The combustion device receives a flow of oxidizer and the second portion of fuel to generate combustion gases. The turbine receives the combustion gases from the combustion device via a fluid circuit. The load device is operably coupled to the turbine via a driveshaft and is configured to receive torque from the driveshaft.
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公开(公告)号：US11060530B2
公开(公告)日：2021-07-13
申请号：US15861811
申请日：2018-01-04
Applicant: General Electric Company
Inventor： Gregory Michael Petrasko , Jeffrey Douglas Rambo
Abstract: A gas turbine engine includes a combustion section and a compressor section, the compressor section including a high pressure compressor. The high pressure compressor includes an aft-most compressor stage and an upstream compressor stage, each of the aft-most compressor stage and the upstream compressor stage including a rotor disk. The gas turbine engine also includes a high pressure spool assembly, the high pressure spool assembly including a rotor disk, and an airflow member extending from the rotor disk of the high pressure spool assembly to the rotor disk of the upstream compressor stage of the high pressure compressor to define in part a compressor cooling air passage outward of the airflow member along a radial direction.
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公开(公告)号：US11434824B2
公开(公告)日：2022-09-06
申请号：US17166245
申请日：2021-02-03
Applicant: General Electric Company
Inventor： Jeffrey Douglas Rambo , Gregory Michael Petrasko
Abstract: A system for energy conversion is provided including a propulsion system, a fuel circuit, a combustion device and turbine separate from the propulsion system, and a load device. A fuel flow control device separates a flow of fuel from the fuel tank into a first portion of fuel and a second portion of fuel. A fuel circuit is configured to provide the first portion of fuel to a heat addition system at the propulsion system. A combustion device receives a flow of oxidizer from a compressor section of the propulsion system via a fluid circuit. The fuel circuit provides the second portion of fuel to the combustion device. The fluid circuit flows combustion gases to the turbine and the propulsion system. The load device is operably coupled to the turbine to receive an output torque via expansion of the combustion gases through the turbine.
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公开(公告)号：US20190203600A1
公开(公告)日：2019-07-04
申请号：US15861811
申请日：2018-01-04
Applicant: General Electric Company
Inventor： Gregory Michael Petrasko , Jeffrey Douglas Rambo
CPC classification number: F01D5/087 , F01D25/12 , F02C3/06 , F02C7/18 , F02C7/28 , F05D2220/3216 , F05D2240/55 , F05D2240/81 , F05D2260/201
Abstract: A gas turbine engine includes a combustion section and a compressor section, the compressor section including a high pressure compressor. The high pressure compressor includes an aft-most compressor stage and an upstream compressor stage, each of the aft-most compressor stage and the upstream compressor stage including a rotor disk. The gas turbine engine also includes a high pressure spool assembly, the high pressure spool assembly including a rotor disk, and an airflow member extending from the rotor disk of the high pressure spool assembly to the rotor disk of the upstream compressor stage of the high pressure compressor to define in part a compressor cooling air passage outward of the airflow member along a radial direction.
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公开(公告)号：US11767793B2
公开(公告)日：2023-09-26
申请号：US17883771
申请日：2022-08-09
Applicant: General Electric Company
Inventor： Jeffrey Douglas Rambo , Gregory Michael Petrasko
CPC classification number: F02C7/224 , B64D37/34 , F02C7/141 , F02C7/16 , F02C7/32 , F02C9/22 , F05D2220/323 , F05D2240/128 , F05D2260/213 , F05D2260/232 , F05D2260/4031 , F05D2260/606 , F05D2260/85
Abstract: A system for energy conversion that includes a propulsion system, a fuel circuit, a combustion device, a turbine, and a load device. The fuel circuit is in fluid communication with a fuel tank and a fuel flow control device that separates a flow of fuel into a first portion and a second portion. The combustion device receives a flow of oxidizer and the second portion of fuel to generate combustion gases. The turbine receives the combustion gases from the combustion device via a fluid circuit. The load device is operably coupled to the turbine via a driveshaft and is configured to receive torque from the driveshaft.
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Patent Agency Ranking
公开(公告)号：US20220243660A1
公开(公告)日：2022-08-04
申请号：US17166245
申请日：2021-02-03
Applicant: General Electric Company
Inventor： Jeffrey Douglas Rambo , Gregory Michael Petrasko
Abstract: A system for energy conversion is provided including a propulsion system, a fuel circuit, a combustion device and turbine separate from the propulsion system, and a load device. A fuel flow control device separates a flow of fuel from the fuel tank into a first portion of fuel and a second portion of fuel. A fuel circuit is configured to provide the first portion of fuel to a heat addition system at the propulsion system. A combustion device receives a flow of oxidizer from a compressor section of the propulsion system via a fluid circuit. The fuel circuit provides the second portion of fuel to the combustion device. The fluid circuit flows combustion gases to the turbine and the propulsion system. The load device is operably coupled to the turbine to receive an output torque via expansion of the combustion gases through the turbine.
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公开(公告)号：US11174789B2
公开(公告)日：2021-11-16
申请号：US15986943
申请日：2018-05-23
Applicant: General Electric Company
Inventor： Jeffrey Douglas Rambo , Gregory Michael Petrasko
Abstract: A gas turbine engine assembly includes a turbomachine including a compressor section, a combustion section, and a turbine section in serial flow order; a fuel delivery system operable with the combustion section of the turbomachine for providing fuel to the combustion section of the turbomachine; and an air cycle assembly including an air cycle machine and a heat exchanger, the air cycle machine in airflow communication with the compressor section of the turbomachine and the heat exchanger in airflow communication with the air cycle machine. The gas turbine engine assembly also includes a thermal transfer bus thermally coupling the heat exchanger of the air cycle assembly to the fuel delivery system for transferring heat from the air cycle machine to the fuel delivery system.
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公开(公告)号：US20250146419A1
公开(公告)日：2025-05-08
申请号：US18500660
申请日：2023-11-02
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Lane Stewart Darby , Joseph Charles Albers , Gregory Michael Petrasko
IPC: F01D5/30
Abstract: A turbine engine has a rotatable disk, a seal cartridge, and a blade. The rotatable disk has a peripheral surface, with at least one slot located in the peripheral surface. The seal cartridge defines a blade seat. The blade has a root, a leading edge and a trailing edge, the root being received within the blade seat.
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公开(公告)号：US20240060451A1
公开(公告)日：2024-02-22
申请号：US18456966
申请日：2023-08-28
Applicant: General Electric Company
Inventor： Jeffrey Douglas Rambo , Gregory Michael Petrasko
CPC classification number: F02C7/224 , F02C7/32 , F02C7/141 , F02C7/16 , F02C9/22 , B64D37/34 , F05D2260/85 , F05D2240/128 , F05D2260/213 , F05D2260/232 , F05D2260/606 , F05D2260/4031 , F05D2220/323
Abstract: A system for energy conversion that includes a propulsion system, a fuel circuit, a combustion device, a turbine, and a load device. The fuel circuit is in fluid communication with a fuel tank and a fuel flow control device that separates a flow of fuel into a first portion and a second portion. The combustion device receives a flow of oxidizer and the second portion of fuel to generate combustion gases. The turbine receives the combustion gases from the combustion device via a fluid circuit. The load device is operably coupled to the turbine via a driveshaft and is configured to receive torque from the driveshaft.
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公开(公告)号：US20230144917A1
公开(公告)日：2023-05-11
申请号：US17883771
申请日：2022-08-09
Applicant: General Electric Company
Inventor： Jeffrey Douglas Rambo , Gregory Michael Petrasko
CPC classification number: F02C7/224 , F02C7/32 , F02C7/141 , F02C7/16 , F02C9/22 , B64D37/34 , F05D2260/85 , F05D2240/128 , F05D2260/213 , F05D2260/232 , F05D2260/606 , F05D2260/4031 , F05D2220/323
Abstract: A system for energy conversion that includes a propulsion system, a fuel circuit, a combustion device, a turbine, and a load device. The fuel circuit is in fluid communication with a fuel tank and a fuel flow control device that separates a flow of fuel into a first portion and a second portion. The combustion device receives a flow of oxidizer and the second portion of fuel to generate combustion gases. The turbine receives the combustion gases from the combustion device via a fluid circuit. The load device is operably coupled to the turbine via a driveshaft and is configured to receive torque from the driveshaft.
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