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    Midshaft rating for turbomachine engines
    2.
    发明授权
    Midshaft rating for turbomachine engines 有权

    公开(公告)号：US12203377B2

    公开(公告)日：2025-01-21

    申请号：US18189740

    申请日：2023-03-24

    Applicant: General Electric Company

    Inventor： Bhaskar Nanda Mondal ,  Narayanan Payyoor ,  Pranav Kamat

    IPC: F01D15/00 ,  F01D5/02 ,  F02C7/06 ,  F02K3/06

    Abstract: A turbomachine engine includes an engine core including a high-pressure compressor, a high-pressure turbine, and a combustion chamber. The engine core has a length (LCORE), and the high-pressure compressor has an exit stage diameter (DCORE). A power turbine is in flow communication with the high-pressure turbine. A low-pressure shaft is coupled to the power turbine and characterized by a midshaft rating from one hundred fifty (ft/sec)1/2 to three hundred thirty (ft/sec)1/2. The low-pressure shaft has a redline speed between fifty and two hundred fifty feet per second. 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. A high-pressure shaft is coupled to the high-pressure compressor and the high-pressure turbine and is characterized by a high-speed shaft rating from 1.5 to 6.2, and a ratio of LCORE/DCORE is from 2.1 to 4.3.

    TURBOMACHINERY ENGINES WITH HIGH-SPEED LOW-PRESSURE TURBINES
    4.
    发明公开
    TURBOMACHINERY ENGINES WITH HIGH-SPEED LOW-PRESSURE TURBINES 审中-公开

    公开(公告)号：US20240337228A1

    公开(公告)日：2024-10-10

    申请号：US18745410

    申请日：2024-06-17

    Applicant: General Electric Company

    Inventor： Pranav R. Kamat ,  Bhaskar Nanda Mondal ,  Jeffrey D. Clements

    IPC: F02K3/06

    CPC classification number: F02K3/06 ,  F05D2200/14

    Abstract: A turbomachinery engine includes a fan assembly, a low-pressure turbine, and a gearbox. The fan assembly includes a plurality of fan blades. The low-pressure turbine includes four rotating stages. The low-pressure turbine includes an area ratio equal to the annular exit area of an aft-most rotating stage of the low-pressure turbine divided by the annular exit area of a forward-most rotating stage of the low-pressure turbine. In some instances, the area ratio is within a range of 2.0-5.1. Additionally (or alternatively) the low-pressure turbine includes an area-EGT ratio within a range of 1.05-1.6.

    MIDSHAFT RATING FOR TURBOMACHINE ENGINES
    9.
    发明申请
    MIDSHAFT RATING FOR TURBOMACHINE ENGINES 有权

    公开(公告)号：US20230136238A1

    公开(公告)日：2023-05-04

    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

    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.

    Compact low-pressure compressor
    10.
    发明授权
    Compact low-pressure compressor 有权

    公开(公告)号：US11549463B2

    公开(公告)日：2023-01-10

    申请号：US17181773

    申请日：2021-02-22

    Applicant: General Electric Company

    Inventor： Vinod Shashikant Chaudhari ,  Bhaskar Nanda Mondal ,  Tsuguji Nakano ,  David W. Crall

    IPC: F02K3/072 ,  F02C3/04 ,  F02C3/08 ,  F02K3/04 ,  F02C7/36 ,  F01D5/02 ,  F02C6/20

    Abstract: Methods, apparatus, systems and articles of manufacture for compact compressors are disclosed including a gas turbine engine defining an axial direction and a radial direction, the gas turbine engine including an axial flow compressor and a radial flow compressor, wherein the axial flow compressor is located axially forward of the radial flow compressor, a blade assembly including a splitter shroud to divide incoming air into axial air flow for the axial flow compressor and radial air flow for the radial flow compressor, the blade assembly rotating relative to the axial flow compressor and counter-rotating relative to the radial flow compressor, and wherein the blade assembly is located axially aft of the radial flow compressor.

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