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    RECUPERATED ENGINE WITH SUPERCRITICAL CO2 BOTTOMING CYCLE
    2.
    发明公开
    RECUPERATED ENGINE WITH SUPERCRITICAL CO2 BOTTOMING CYCLE 审中-公开

    公开(公告)号：US20230313711A1

    公开(公告)日：2023-10-05

    申请号：US18109448

    申请日：2023-02-14

    Applicant: RAYTHEON TECHNOLOGIES CORPORATION

    Inventor： Malcolm P. MacDonald ,  Stephen H. Taylor ,  Ram Ranjan

    IPC: F01K23/10 ,  F01K25/10

    CPC classification number: F01K23/10 ,  F01K25/103 ,  F05D2260/211 ,  F05D2220/76 ,  F05D2260/213

    Abstract: A gas turbine engine includes a core engine that includes a core flow path that connects a compressor section, combustor section and a turbine section. The gas turbine engine further includes a bottoming cycle system that includes a supercritical CO2 (sCO2) working fluid flow. A first recuperator is disposed in the core flow path downstream of the turbine section, the first recuperator is configured to transfer thermal energy from a core flow aft of the turbine section to the sCO2 working fluid flow. A second recuperator is disposed in the compressor section, the second recuperator is configured to transfer thermal energy from the sCO2 working fluid flow to a location forward of the combustor section.

    Adjustable primary and supplemental power units
    4.
    发明授权
    Adjustable primary and supplemental power units 有权

    公开(公告)号：US11970970B2

    公开(公告)日：2024-04-30

    申请号：US18109441

    申请日：2023-02-14

    Applicant: RAYTHEON TECHNOLOGIES CORPORATION

    Inventor： Malcolm P. MacDonald ,  Stephen H. Taylor

    IPC: F02C6/18 ,  B64D27/10 ,  B64D33/08

    CPC classification number: F02C6/18 ,  B64D27/10 ,  B64D33/08

    Abstract: A propulsion system for an aircraft includes a core flow path in communication with a compressor section, combustor section and a turbine section. A first bottoming cycle system includes a bottoming working fluid flow in thermal communication with a high energy exhaust gas flow that is generated by the core engine. The first bottoming cycle is configured to recover power from the high energy exhaust gas flow in a first engine operating condition and in a second engine operating condition. A second bottoming cycle system is configured to recover power from the high energy exhaust gas flow in the first engine operating condition and not to recover power in a second engine operating condition.

    AIR BOTTOMING CYCLE DRIVEN PROPULSOR
    5.
    发明公开
    AIR BOTTOMING CYCLE DRIVEN PROPULSOR 审中-公开

    公开(公告)号：US20240117764A1

    公开(公告)日：2024-04-11

    申请号：US17951991

    申请日：2022-09-23

    Applicant: RAYTHEON TECHNOLOGIES CORPORATION

    Inventor： Stephen H. Taylor ,  Alan Retersdorf ,  Oliver V. Atassi

    IPC: F02C9/18 ,  F02C7/32 ,  F02C7/36

    CPC classification number: F02C9/18 ,  F02C7/32 ,  F02C7/36 ,  F05D2220/323 ,  F05D2220/36

    Abstract: An aircraft propulsion system includes a core engine that includes a core flow path where a core airflow is compressed in a compressor section, communicated to a combustor section, mixed with fuel and ignited to generate a gas flow that is expanded through a turbine section for powering a primary propulsor. The aircraft propulsion system further includes a tap that is at a location upstream of the combustor section where a bleed airflow is drawn, a heat exchanger where the bleed airflow is heated by the gas flow, a power turbine through which heated bleed airflow is expanded to generate a work output, and a secondary propulsor that is driven by the work output that is generated by the power turbine.

    Turbine engine bleed waste heat recovery
    7.
    发明授权
    Turbine engine bleed waste heat recovery 有权

    公开(公告)号：US11702981B1

    公开(公告)日：2023-07-18

    申请号：US17724904

    申请日：2022-04-20

    Applicant: RAYTHEON TECHNOLOGIES CORPORATION

    Inventor： Stephen H. Taylor ,  Alan Retersdorf

    IPC: F02C6/08 ,  F02C9/18 ,  F02C3/10 ,  F02C7/14 ,  F02C7/18 ,  F02C7/36

    CPC classification number: F02C6/08 ,  F02C3/10 ,  F02C7/14 ,  F02C7/18 ,  F02C9/18 ,  F02C7/36

    Abstract: A gas turbine engine assembly includes a core engine that includes a core flow path where a core airflow is compressed in a compressor section, communicated to a combustor section, mixed with fuel and ignited to generate a high energy combusted gas flow that is expanded through a turbine section, a first tap at a location up stream of the combustor section for communicating a portion of the core airflow as a bleed airflow downstream of the combustor section, a heat exchanger that places the bleed airflow that is communicated from the first tap in thermal communication with the high energy combusted gas flow downstream of the combustor section, and a power turbine that is configured to generate shaft power from expansion of the heated bleed airflow, the power turbine includes an inlet that is configured to receive the heated bleed airflow from the heat exchanger.

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