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    Gas turbine engine
    3.
    发明授权
    Gas turbine engine 有权

    公开(公告)号：US11512644B2

    公开(公告)日：2022-11-29

    申请号：US17369332

    申请日：2021-07-07

    申请人： ROLLS-ROYCE plc

    发明人： Graham P Bruce ,  Stephen M Husband ,  David F Brookes

    IPC分类号： F02C7/268

    摘要： Gas turbine engines and methods of starting gas turbine engines, the gas turbine engine including: an electronic engine controller; one or more spools designated a starting spool for starting the engine, and has a required starting torque τs; a permanent magnet alternator mechanically coupled with the starting spool, the alternator, in a motor mode, provides a peak torque of τa, and, in a generator mode, generates electrical power for the electronic engine controller; and an electrical starter-generator mechanically coupled with the starting spool. The starter-generator in a motor mode, provides a peak torque of τsg, and, in a generator mode, generates electrical power for an external load. τsg+τa≥τs and τsg, τa

    Electrical system having two rotary electric machines coupled to two gas turbine spools
    6.
    发明授权
    Electrical system having two rotary electric machines coupled to two gas turbine spools 有权

    公开(公告)号：US11532937B2

    公开(公告)日：2022-12-20

    申请号：US17002086

    申请日：2020-08-25

    申请人： ROLLS-ROYCE plc

    发明人： David F Brookes ,  Graham P Bruce ,  Stephen M Husband

    IPC分类号： H02J1/10 ,  F02C3/113 ,  H02J3/14 ,  H02M1/10 ,  F02C7/36

    摘要： Electrical systems for connecting rotary electric machines with gas turbine spools are provided. One such electrical system comprises: a first rotary electric machine mechanically coupled with a first gas turbine spool and a second rotary electric machine mechanically coupled with a second gas turbine spool, each said electric machine having an identical even number N≥4 of phases, each phase having a respective index n=(1, . . . , N), and each phase comprising an identical number P≥1 of coils wound in a P-plex configuration in which adjacent phases are radially separated by 2π/NP mechanical radians; a first set of N bidirectional converter circuits for conversion of alternating current (ac) to and from direct current (dc), each converter circuit having a respective index n and being connected with the P coils in the nth phase of the first rotary electric machine; and a second set of N bidirectional converter circuits for conversion of ac to and from dc, each converter circuit having a respective index n and being connected with the P coils in the nth phase of the second rotary electric machine. For all n, a dc side of the nth converter circuit in said first set is connected with a dc side of the nth converter circuit in said second set to facilitate dc power transfer between the first gas turbine spool and the second gas turbine spool.

    Gas turbine engine
    7.
    发明授权
    Gas turbine engine 有权

    公开(公告)号：US11879413B2

    公开(公告)日：2024-01-23

    申请号：US17940480

    申请日：2022-09-08

    申请人： ROLLS-ROYCE plc

    发明人： Paul R Davies ,  Gareth E Moore ,  Stephen M Husband ,  David R Trainer ,  David P Scothern ,  Luke George

    IPC分类号： F02K3/06 ,  F01D15/10 ,  F02C7/141

    CPC分类号： F02K3/06 ,  F01D15/10 ,  F02C7/141 ,  F05D2220/323 ,  F05D2220/36 ,  F05D2260/213 ,  F05D2260/606

    摘要： An aircraft gas turbine engine includes a heat exchanger module, and a core engine. The core engine includes an intermediate-pressure compressor, high-pressure compressor, and high and low-pressure turbines. The high-pressure compressor rotationally connects to the high-pressure turbine by a first shaft, and the intermediate-pressure compressor rotationally connects to the low-pressure turbine by a second shaft. The heat exchanger module fluidly communicates with the core engine by an inlet duct. The heat exchanger module includes a central hub and multiple heat transfer elements extending radially from the hub and spaced in a circumferential array, for heat energy transfer from a first fluid within the elements to an inlet airflow passing over a surface of the elements prior to airflow entry into an inlet to the core engine. The gas turbine engine further includes a first electric machine rotationally connected to the first shaft, and positioned downstream of the heat exchanger module.