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    Sensor fault detection method
    2.
    发明授权
    Sensor fault detection method 有权

    公开(公告)号：US10132192B2

    公开(公告)日：2018-11-20

    申请号：US15637000

    申请日：2017-06-29

    Applicant: ROLLS-ROYCE PLC

    Inventor： David P Scothern

    IPC: F01D21/00 ,  G01K13/02 ,  G01L27/00 ,  G01K15/00

    Abstract: A method of determining a faulty sensor of a sensor array of a gas turbine engine, the sensor array including at least first, second and third sensors, the method including the steps of: measuring a first set of sensor outputs prior to engine startup from each sensor, and calculating a first difference in the measured value for each sensor pair; after a period of time, measuring a second set of sensor outputs prior to engine startup from each sensor, and calculating a second difference in measured value for each sensor pair; calculating a further difference between the calculated first and second differences for each sensor pair; and identifying a failed sensor where two or more sensor pairs including a common sensor have a further difference above a predetermined threshold.

    Seal
    4.
    发明授权
    Seal 有权

    公开(公告)号：US10119420B2

    公开(公告)日：2018-11-06

    申请号：US15171577

    申请日：2016-06-02

    Applicant: ROLLS-ROYCE plc

    Inventor： David P Scothern

    IPC: F16J15/40 ,  F16J15/42 ,  F01D25/18 ,  F02C7/28 ,  F01D11/04 ,  F01D11/00 ,  F01D11/10

    Abstract: A hydraulic seal arrangement including first and second rotatable components, the first defining a first annular trough defined by radially inwardly extending first and second walls, the second component defining a radially outwardly extending web between the walls. The first component includes a second trough defined by the second wall and a third wall axially spaced from the second, the second trough defining an open radially inner end defined by a radially inner end of the second wall such that the first and second annular troughs fluidly communicate around the circumference of the first component via the inner end of the second wall. At a first circumferential position, the second wall of the first component defines a second trough oil inlet providing further fluid communication between the first and second troughs and at a second circumferential position, the third wall of the first component defines a second trough oil outlet.

    Gas turbine engine
    5.
    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

    Applicant: ROLLS-ROYCE plc

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

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

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

    Abstract: 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.

    Hybrid aircraft propulsion system
    6.
    发明授权
    Hybrid aircraft propulsion system 有权

    公开(公告)号：US11407517B2

    公开(公告)日：2022-08-09

    申请号：US16394280

    申请日：2019-04-25

    Applicant: ROLLS-ROYCE plc

    Inventor： David P Scothern

    IPC: B64D27/12 ,  B64D27/24 ,  F01D15/10 ,  F02C6/20 ,  B64D27/02

    Abstract: A hybrid aircraft propulsion system. The system comprises a gas turbine engine comprising a compressor, a combustor, one or more turbines, a shaft coupled to one of the turbines, and a bypass fan mechanically driven by the shaft. The system further comprises an electrical generator mechanically coupled to the shaft, and an auxiliary propulsor mechanically coupled to an electric motor and electrically coupled to the electric generator. At maximum power, the gas turbine engine is configured to produce a turbine entry temperature at maximum power between 1800 Kelvin and 2000 Kelvin, the engine comprises a fan bypass ratio of between 4:1 and 13:1, and the generator is configured to absorb between 10% and 60% of the mechanical power generated by the turbine.

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