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    DRIVE SHAFT ASSEMBLY
    1.
    发明申请
    DRIVE SHAFT ASSEMBLY 审中-公开
    驱动轴组件

    公开(公告)号：US20170002869A1

    公开(公告)日：2017-01-05

    申请号：US15172977

    申请日：2016-06-03

    Applicant: ROLLS-ROYCE plc

    Inventor： Wen Yao LEE ,  Anthony H. SIMPSON ,  Pranav AGGARWAL ,  David P. SCOTHERN ,  Andrew SWIFT

    IPC: F16D3/06 ,  F02C7/36 ,  F16C3/02

    CPC classification number: F16D3/06 ,  F02C7/36 ,  F05D2260/40311 ,  F16C3/02 ,  F16D1/10 ,  F16D9/00 ,  F16D2001/103

    Abstract: A drive shaft assembly comprising a first shaft and a second shaft is disclosed. The second shaft is axially translatable from an engaged configuration with the first shaft at one limit of its travel to a disengaged configuration from the first shaft at the opposite limit of its travel. Engagement of the first and second shafts is via cooperating helical splines provided thereon. The helical splines give rise to a disengaging axial force on the second shaft in a fault condition in which a driving torque is applied from one of the first and second shafts to the helical splines in a rotational direction tending to unscrew the helical splines. Consequently when the second shaft is in the engaged configuration the disengaging axial force translates the second shaft to the disengaged configuration.

    Abstract translation: 公开了一种包括第一轴和第二轴的传动轴组件。 第二轴可以从接合构型轴向平移，其中第一轴在其行进的一个极限处以与其行进的相反极限处的第一轴分离的构型。 第一和第二轴的接合是通过配合在其上的螺旋花键。 螺旋花键在故障状态下产生在第二轴上的分离轴向力，其中驱动扭矩从第一和第二轴之一施加到沿着倾斜螺旋花键的旋转方向的螺旋花键。 因此，当第二轴处于接合构型时，分离轴向力将第二轴平移到分离构型。

    GAS TURBINE ENGINE COUPLING ARRANGEMENT
    2.
    发明申请
    GAS TURBINE ENGINE COUPLING ARRANGEMENT 审中-公开

    公开(公告)号：US20190360403A1

    公开(公告)日：2019-11-28

    申请号：US16410312

    申请日：2019-05-13

    Applicant: ROLLS-ROYCE plc

    Inventor： Andrew SWIFT ,  Stewart T. THORNTON

    IPC: F02C7/32 ,  F16H57/023 ,  F16H57/021

    Abstract: A coupling arrangement for a gas turbine engine. The arrangement comprises first, second and third members. The first member has a first threaded mating surface extending in a first direction (X) and a flange extending in a direction generally normal to the first direction (X). The second member has a second threaded mating surface extending in the first direction (X) and a flange extending in a direction generally normal to the first direction (X), the flanges of the first and second members engaging against one another. The third member has a third threaded mating surface configured to engage against the first threaded mating surface, and a fourth threaded mating surface configured to engage against the second threaded mating surface.

    GAS TURBINE ENGINE
    6.
    发明申请
    GAS TURBINE ENGINE 审中-公开

    公开(公告)号：US20200040845A1

    公开(公告)日：2020-02-06

    申请号：US16398772

    申请日：2019-04-30

    Applicant: ROLLS-ROYCE plc

    Inventor： Andrew SWIFT

    IPC: F02K3/02 ,  B64D27/10 ,  F02C7/36 ,  F02K1/46

    Abstract: An aircraft gas turbine engine includes a compressor system including a low pressure compressor coupled to a low pressure shaft, and a high pressure compressor coupled to a high pressure shaft. An inner core casing is provided radially inwardly of compressor blades of the compressor system. A fan is coupled to the low pressure shaft via a reduction gearbox. The high pressure compressor includes an outer core casing arrangement provided radially outwardly of compressor blades of the high pressure compressor, the inner and outer core casing arrangements defining a core working gas flow path therebetween; and the outer core casing arrangement includes a first and a second outer core casing spaced radially outward from the first outer core casing. At an axial plane of an inlet to the high pressure compressor, the second outer core casing has a radius greater than 0.25 times a radius of the fan.

    GEARED TURBOFAN GAS TURBINE ENGINE MOUNTING ARRANGEMENT
    7.
    发明申请
    GEARED TURBOFAN GAS TURBINE ENGINE MOUNTING ARRANGEMENT 审中-公开

    公开(公告)号：US20200032674A1

    公开(公告)日：2020-01-30

    申请号：US16453100

    申请日：2019-06-26

    Applicant: ROLLS-ROYCE plc

    Inventor： Andrew SWIFT

    IPC: F01D25/28 ,  F01D25/24 ,  F02C7/36 ,  B64D27/12 ,  B64D29/02 ,  B64D29/06

    Abstract: An aircraft gas turbine engine includes an engine core including a turbine, a compressor, a core shaft connecting the turbine to compressor, and a core casing surrounding the engine core. A fan is located upstream of the engine core and fan casing surrounds the fan. A gearbox receives input from the core shaft and outputs drive to rotate the fan. A single plane support structure connects the core and fan casing. The support structure includes an inner ring, outer ring and plurality of circumferentially spaced radially extending struts connecting the inner and outer ring. The inner ring including a torsion box and a gearbox and fan support structure is connected to the torsion box. A front and rear mount are configured to connect the gas turbine engine to the aircraft, wherein the front mount is coupled to the torque box and the rear mount is coupled to the core casing.

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