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    TURBOMACHINERY ENGINES WITH HIGH-SPEED LOW-PRESSURE TURBINES
    2.
    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.

    OPEN ROTOR TURBOMACHINERY ENGINES
    5.
    发明申请
    OPEN ROTOR TURBOMACHINERY ENGINES 有权

    公开(公告)号：US20220259985A1

    公开(公告)日：2022-08-18

    申请号：US17176106

    申请日：2021-02-15

    Applicant: General Electric Company

    Inventor： Timothy Richard DePuy ,  Trevor Goerig ,  Jeffrey D. Clements ,  Syed Arif Khalid

    IPC: F01D15/12 ,  F02C6/20

    Abstract: A turbomachinery engine includes an unducted rotor assembly, a low-pressure turbine, a low-pressure shaft, a gearbox, and an engine correlation parameter. The unducted rotor assembly includes a plurality of rotor blades arranged in a single row and defining a blade diameter. The gearbox includes an input, an output, and a gear ratio. The input of the gearbox is coupled to the low-pressure shaft (which is coupled to the LPT), and the output of the gearbox is coupled to the unducted rotor assembly. The engine correlation parameter is greater than 0.17 and less than 0.83. The engine correlation parameter equals D/N/GR, where D is the blade tip diameter measured in feet, N is the stage count of the low-pressure turbine, and GR is the gear ratio of the gearbox. The unducted propulsor assembly optionally includes a disk loading within a range of 60-180 HP/ft2 at a takeoff flight condition.

    Method of operating a turbine engine having a bleed system
    6.
    发明授权
    Method of operating a turbine engine having a bleed system 有权

    公开(公告)号：US12276229B2

    公开(公告)日：2025-04-15

    申请号：US18463800

    申请日：2023-09-08

    Applicant: General Electric Company

    Inventor： Brandon W. Miller ,  Geoffrey Whitener ,  Jeffrey D. Clements ,  Patrick Marrinan ,  Andrew J. Hank

    IPC: F02C9/18

    Abstract: A method of operating a turbine engine. The turbine engine includes a high-pressure compressor including a high-pressure compressor flowpath and a plurality of stages, and a bleed system. The bleed system includes a plurality of bleed flowpaths including a first bleed flowpath from one stage of the plurality of stages and a second bleed flowpath from another stage of the plurality of stages. The method includes directing compressed air through the high-pressure compressor flowpath, directing a first portion of the compressed air through the first bleed flowpath, the first portion of the compressed air having a first mass flow, directing a second portion of the compressed air through the second bleed flowpath, determining an altitude of the turbine engine, and changing the first mass flow of the first portion of the compressed air through the first bleed flowpath based on the altitude of the turbine engine.

    Overall engine efficiency rating for turbomachine engines
    9.
    发明授权
    Overall engine efficiency rating for turbomachine engines 有权

    公开(公告)号：US12049849B2

    公开(公告)日：2024-07-30

    申请号：US18209689

    申请日：2023-06-14

    Applicant: General Electric Company ,  GE Avio S.r.l.

    Inventor： Andrea Piazza ,  Jeffrey D. Clements

    IPC: F02C7/36 ,  F02C3/067 ,  F02K3/06

    CPC classification number: F02C7/36 ,  F02C3/067 ,  F02K3/06 ,  F05D2200/13 ,  F05D2200/14 ,  F05D2200/221 ,  F05D2260/40311 ,  F05D2260/98

    Abstract: A turbomachine engine can include a fan assembly, a vane assembly, a core engine, a gearbox, and an overall engine efficiency rating. The fan assembly can include a plurality of fan blades. The vane assembly can include a plurality of vanes, and the vanes can, in some instances, be disposed aft of the fan blades. The core engine can include a low-pressure turbine. The gearbox includes an input and an output. The input of the gearbox is coupled to the low-pressure turbine of the core engine and comprises a first rotational speed, the output of the gearbox is coupled to the fan assembly and has a second rotational speed, and a gear ratio of the first rotational speed to the second rotational speed is within a range of 2.0-4.0. The overall engine efficiency rating is greater than or equal to 0.35GR1.5 and less than or equal to 0.7GR1.5.

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