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    GAS TURBINE ENGINE VANES
    2.
    发明申请
    GAS TURBINE ENGINE VANES 审中-公开

    公开(公告)号：US20180252113A1

    公开(公告)日：2018-09-06

    申请号：US15907538

    申请日：2018-02-28

    Applicant: ROLLS-ROYCE plc

    Inventor： Richard NORTHALL ,  Anthony J. RAE ,  Michael S. KRAUTHEIM ,  Alastair D. WALKER ,  Jonathan F. CARROTTE ,  Ian MARIAH

    IPC: F01D9/04 ,  F01D5/14

    Abstract: An annular array of turning vanes 200 is provided in a duct 100 of a gas turbine engine 10. The annular array of turning vanes 200 comprises aerodynamic vanes 220 and strut-vanes 240. The strut-vanes 240 have greater chord length and extend further axially downstream than the aerodynamic vanes 220. The leading edge of the strut-vanes 240 is upstream of the trailing edge of the aerodynamic vanes 220. The strut-vanes provide flow turning. The space to chord ratio of the aerodynamic vanes that are closest to the suction surface of a strut-vane is higher than the space to chord ratio of aerodynamic vanes that are closest to a pressure surface of the strut-vane. The arrangement allows the duct 100 to be axially short.

    FUEL INJECTOR
    3.
    发明申请
    FUEL INJECTOR 审中-公开
    喷油器

    公开(公告)号：US20170009991A1

    公开(公告)日：2017-01-12

    申请号：US15179495

    申请日：2016-06-10

    Applicant: ROLLS-ROYCE plc

    Inventor： Jonathan F. CARROTTE ,  Stephen C. HARDING ,  Ashley G. BARKER

    IPC: F23R3/20 ,  F23R3/34 ,  F02C7/22

    CPC classification number: F23R3/20 ,  F02C7/222 ,  F23D11/107 ,  F23D2206/10 ,  F23D2900/11401 ,  F23R3/343 ,  F23R2900/00014

    Abstract: A fuel injection system for a gas turbine engine (10) comprises; a pilot fuel injector section (22, 23) and a main airblast fuel injector section (25, 26, 27, 28, 29), the main airblast fuel injector section having an aft end (29) facing a combustion chamber (30). A surface of the injection system exposed to air flow through an injection system is non-axisymmetric or non-planar in a reference circumferential plane and/or is configured to generate controlled and varying acoustic impedance at or adjacent the aft end where, in use, the air flow collides with an oncoming acoustic wave.

    Abstract translation: 一种用于燃气涡轮发动机（10）的燃料喷射系统，包括： 主燃料喷射器部分（22,23）和主喷气燃料喷射器部分（25,26,27,28,29），主喷油器燃料喷射器部分具有面向燃烧室（30）的后端（29）。 暴露于通过注射系统的空气流动的注射系统的表面在参考圆周平面中是非轴对称的或非平面的，和/或被构造成在后端或邻近尾端处产生受控和变化的声阻抗， 空气流与迎面而来的声波相撞。

    FUEL INJECTION
    4.
    发明申请
    FUEL INJECTION 有权

    公开(公告)号：US20220099025A1

    公开(公告)日：2022-03-31

    申请号：US17476174

    申请日：2021-09-15

    Applicant: ROLLS-ROYCE plc

    Inventor： Jonathan F. CARROTTE ,  Anthony John MORAN ,  Mark BREND ,  Mark CASSELL ,  Maxwell WILLIAMS

    IPC: F02C7/22 ,  F02C7/04 ,  F23R3/04

    Abstract: A direct injection fuel system is shown for injecting hydrogen fuel into a gas turbine combustor. The fuel injection system includes a plurality of fuel injector blocks. Each fuel injector block includes a fuel admission duct having an inlet for receiving hydrogen fuel from a fuel supply, an outlet for delivering hydrogen fuel into the combustor and a central axis extending from said inlet to said outlet. Each fuel injector block also includes an air admission duct located around the periphery of the fuel admission duct, having an inlet for receiving air from a diffuser and an outlet for delivering air into the combustor for mixing with the hydrogen fuel.

    FUEL INJECTOR FOR A GAS TURBINE ENGINE COMBUSTION CHAMBER
    6.
    发明申请
    FUEL INJECTOR FOR A GAS TURBINE ENGINE COMBUSTION CHAMBER 审中-公开

    公开(公告)号：US20170089582A1

    公开(公告)日：2017-03-30

    申请号：US15247340

    申请日：2016-08-25

    Applicant: ROLLS-ROYCE plc

    Inventor： Jonathan F. CARROTTE ,  Christopher L. FORD

    IPC: F23R3/16 ,  F02C3/04

    CPC classification number: F23R3/16 ,  F02C3/04 ,  F05D2240/35 ,  F05D2260/14 ,  F23C2900/07001 ,  F23D2900/11101 ,  F23R3/14 ,  F23R3/286 ,  F23R3/343

    Abstract: A fuel injector includes a central member arranged on axis of fuel injector and a first member arranged around central member. A first swirler is arranged between central member and first member. A pilot fuel injector is arranged to supply fuel onto inner surface of first member. A second member is arranged between downstream end of first member and downstream end of shroud. A second swirler is arranged between upstream end of first member and upstream end of shroud and between downstream end of first member and upstream end of second member. A third swirler is arranged between downstream end of shroud and second member. A main fuel injector is arranged to supply fuel into an annular passage between first member and second member and a fourth swirler extends through first member.

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