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    FLOW-METERING FUEL SYSTEMS AND RELATED METHODS
    5.
    发明公开
    FLOW-METERING FUEL SYSTEMS AND RELATED METHODS 审中-公开

    公开(公告)号：EP4336027A1

    公开(公告)日：2024-03-13

    申请号：EP22194974.6

    申请日：2022-09-09

    申请人： General Electric Company ,  Ge Avio S.r.l.

    发明人： MURRAY, Michael ,  GERNONE, Mirko

    IPC分类号： F02C3/20 ,  F02C9/26 ,  F02C9/28 ,  F02C9/40

    摘要： Flow-metering fuel systems and related methods are disclosed. An example apparatus (200, 300, 400, 500, 900) includes a pipe (210, 302, 402, 406, 410, 414, 502, 506, 508, 600, 700, 800) defining a flow path for fuel, the pipe fluidly coupled to a combustor (202), a first portion (602) of the pipe having a first cross-sectional area (A1), a second portion (606) of the pipe having a second cross-sectional area (A2) smaller than the first cross-sectional area, the second portion downstream of the first portion, and an actuator (316, 318, 320, 422, 424, 426) to adjust a flow rate of the fuel in the pipe based on a first pressure of the fuel in the first portion of the pipe, a second pressure of the fuel in the second portion of the pipe, and a temperature of the fuel.

    GAS TURBINE COMBUSTOR STRUCTURE
    6.
    发明公开
    GAS TURBINE COMBUSTOR STRUCTURE 审中-公开

    公开(公告)号：EP4332438A1

    公开(公告)日：2024-03-06

    申请号：EP22795615.8

    申请日：2022-04-18

    申请人： Toshiba Energy Systems & Solutions Corporation

    发明人： KASUYA, Hiroki ,  ITOH, Masao ,  IWAI, Yasunori ,  MORISAWA, Yuichi ,  SASAKI, Takashi

    IPC分类号： F23R3/12 ,  F02C3/20 ,  F02C3/30 ,  F23R3/00 ,  F23R3/28 ,  F23R3/44

    摘要： A combustor structure 1 of an embodiment includes: a plurality of combustors 50; a rear liner 60 which guides a combustion gas from the plurality of combustors 50 to a downstream side; and a scroll 70 which guides the combustion gas from the rear liner 60 in an axial direction and a circumferential direction of a turbine rotor 97. Each of the combustors 50 includes: a combustor liner 51; a fuel supply part 52 which supplies fuel into the combustor liner; and an oxidant supply part 53 which supplies a swirling flow of an oxidant from the circumference of the fuel supply part 52 into the combustor liner. The plurality of combustors 50 include: the combustor 50 in which a swirling direction of the swirling flow of the oxidant is clockwise; and the combustor 50 in which a swirling direction of the swirling flow of the oxidant is counterclockwise.

    COMBUSTION CHAMBER WITH SOLID FUEL
    9.
    发明公开
    COMBUSTION CHAMBER WITH SOLID FUEL 审中-公开

    公开(公告)号：EP3848566A1

    公开(公告)日：2021-07-14

    申请号：EP21150616.7

    申请日：2021-01-07

    申请人： Raytheon Technologies Corporation

    发明人： O'FLARITY, Steven M.

    IPC分类号： F02C3/22 ,  C01B3/00 ,  F02C3/20 ,  F02M21/02

    摘要： A propulsion system (101) is provided and includes a solid hydride storage unit (110) from which gaseous hydrogen fuel is drawn, an engine (120) comprising a combustion chamber (121) and a piping system to draw the gaseous hydrogen fuel from the solid hydride storage unit, the piping system being interposed between the solid hydride storage unit and the combustion chamber. The combustion chamber is receptive of the gaseous hydrogen fuel drawn from the solid hydride storage unit by the piping system and is configured to combust the gaseous hydrogen fuel to drive an operation of the engine.