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    GAS TURBINE ENGINE HAVING A HEAT ABSORPTION DEVICE AND AN ASSOCIATED METHOD THEREOF
    71.
    发明申请
    GAS TURBINE ENGINE HAVING A HEAT ABSORPTION DEVICE AND AN ASSOCIATED METHOD THEREOF 审中-公开

    公开(公告)号：US20190078516A1

    公开(公告)日：2019-03-14

    申请号：US15702730

    申请日：2017-09-12

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Karthikeyan Sampath ,  Atanu Saha ,  Bhaskar Nanda Mondal ,  Sanjeev Sai Kumar Manepalli

    IPC: F02C7/16 ,  F02C7/14 ,  B64D33/08

    Abstract: A gas turbine engine having a heat absorption device and an associated method are disclosed. The gas turbine engine includes a compressor, a combustor, a turbine, a bleed fluid cavity, and the heat absorption device. The combustor is coupled to the compressor. The turbine is coupled to the compressor and the combustor. The bleed fluid cavity is formed at a first predefined location in the compressor. The heat absorption device is disposed in the bleed fluid cavity and includes a casing, a flow path, and a phase change material. The casing includes an inlet and an outlet. The flow path is within the casing, extends between the inlet and the outlet, and directs an input bleed fluid separated from a fluid stream discharged from the compressor. The phase change material is filled in the casing, separated from the flow path.

    TURBINE ENGINE WITH THREE AIR STREAMS
    75.
    发明申请
    TURBINE ENGINE WITH THREE AIR STREAMS 有权

    公开(公告)号：US20250129741A1

    公开(公告)日：2025-04-24

    申请号：US18417814

    申请日：2024-01-19

    Applicant: General Electric Company

    Inventor： Jeffrey D. Rambo ,  Bhaskar Nanda Mondal

    IPC: F02C3/30 ,  F02C7/18 ,  F02C9/18

    Abstract: A turbine engine includes a cooling air duct for cooling air positioned radially between a core air flow path for core air and a bypass airflow passage for bypass air. A heat exchanger is positioned in the cooling air duct to transfer heat from a heat source from within the turbine engine. The heat exchanger may be a condenser. The turbine engine may further include a steam system that extracts water from the combustion gases, vaporizes the water to generate steam, and injects the steam into the core air flow path, the steam system including the condenser to transfer heat from the combustion gases to the cooling air and to condense the water from the combustion gases. The turbine engine may further include a booster fan to increase the pressure of the cooling air and the core air.

    Midshaft rating for turbomachine engines
    79.
    发明授权
    Midshaft rating for turbomachine engines 有权

    公开(公告)号：US12071978B2

    公开(公告)日：2024-08-27

    申请号：US18058036

    申请日：2022-11-22

    Applicant: General Electric Company

    Inventor： Narayanan Payyoor ,  Bhaskar Nanda Mondal

    IPC: F16C3/02 ,  F02C7/06

    CPC classification number: F16C3/02 ,  F02C7/06 ,  F05D2240/60 ,  F16C2360/23

    Abstract: A turbomachine engine including an engine core including a high-pressure compressor, which has an exit stage having an exit stage diameter (DCORE), a high-pressure turbine, and a combustion chamber in flow communication with the high-pressure compressor and the high-pressure turbine, a power turbine in flow communication with the high-pressure turbine, and a low-pressure shaft coupled to the power turbine and characterized by a midshaft rating (MSR) between two hundred (ft/sec)1/2 and three hundred (ft/sec)1/2. The low-pressure shaft has a redline speed between fifty and two hundred fifty feet per second (ft/sec). The turbomachine engine is configured to operate up to the redline speed without passing through a critical speed associated with a first-order bending mode of the low-pressure shaft. The low-pressure shaft has a length (LMSR) defined by an engine core length (LCORE) given by: LCORE=[m(20+m)*n(10+n)](1/100)*DCORE+CIS.

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