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    Engine mount
    1.
    发明授权
    Engine mount 有权

    公开(公告)号：US09809317B2

    公开(公告)日：2017-11-07

    申请号：US14543402

    申请日：2014-11-17

    Applicant: ROLLS-ROYCE PLC

    Inventor： Richard Geoffrey Stretton ,  Kenneth Franklin Udall

    IPC: B64D27/26 ,  F02C7/20 ,  B64D27/10

    CPC classification number: B64D27/26 ,  B64D27/10 ,  B64D2027/262 ,  F02C7/20 ,  F05D2220/325 ,  F05D2250/11

    Abstract: An aircraft including a pylon attached to a gas turbine engine and a mounting system attaching the engine to the pylon. The mounting system including a first and a second frame each of three elongate members arranged in a triangle, each frame respectively arranged such that a core of the engine is positioned extending through an area defined between the three elongate members of each frame. Each frame forming at least part of a load bearing connection between the pylon and the engine. Each frame consisting of two portions, each portion corresponding to each side of the engine as attached to the pylon. The triangle formed by each frame being symmetrical about a plane separating the two portions. The engine is attached to the mounting system such that both frames are positioned axially forward of a radially extending projection of a first turbine stage in the core.

    Gas turbine engine
    4.
    发明授权
    Gas turbine engine 有权
    燃气轮机

    公开(公告)号：US09387923B2

    公开(公告)日：2016-07-12

    申请号：US13914882

    申请日：2013-06-11

    Applicant: ROLLS-ROYCE PLC

    Inventor： Richard Geoffrey Stretton ,  Nicholas Howarth

    IPC: B64C11/00 ,  F02C3/067

    CPC classification number: B64C11/001 ,  B64D27/00 ,  B64D2027/005 ,  F02C3/067 ,  F02C7/04 ,  F02C7/05 ,  F02K3/025 ,  F02K3/04 ,  F05D2220/323 ,  F05D2220/325 ,  F05D2240/302 ,  F05D2250/324 ,  F05D2250/51 ,  Y02T50/66 ,  Y02T50/671 ,  Y02T50/673

    Abstract: A gas turbine engine (10) having an axial flow direction (X) therethrough in use. The gas turbine engine (10) comprises one or more rotor stages each comprising at least one rotor blade (120) having a root portion (122). The gas turbine engine (10) comprises a shroud (122) located upstream of one or more of the rotor stages relative to the axial flow direction (X). The shroud (122) defines a through passageway (128) extending between an inlet (130) and an outlet (132) which comprises a diffuser region (138). The diffuser region (138) is configured to reduce the axial velocity of air exiting the outlet (132) relative to air entering the diffuser portion (138) in use, wherein the outlet (132) is located such that air exiting the outlet (132) is directed substantially to the root portion (122) only of the rotor blades (120).

    Abstract translation: 一种在使用中具有轴流动方向（X）的燃气轮机（10）。 燃气涡轮发动机（10）包括一个或多个转子级，每个转子级包括至少一个具有根部（122）的转子叶片（120）。 燃气涡轮发动机（10）包括相对于轴向流动方向（X）定位在一个或多个转子级的上游的护罩（122）。 护罩（122）限定在入口（130）和包括扩散器区域（138）的出口（132）之间延伸的通道（128）。 扩散器区域（138）构造成在使用时相对于进入扩散器部分（138）的空气减少离开出口（132）的空气的轴向速度，其中出口（132）定位成使得离开出口（132）的空气 ）仅基本上指向转子叶片（120）的根部（122）。

    Aircraft engine mount
    6.
    发明授权
    Aircraft engine mount 有权

    公开(公告)号：US09701412B2

    公开(公告)日：2017-07-11

    申请号：US14474760

    申请日：2014-09-02

    Applicant: ROLLS-ROYCE PLC

    Inventor： Richard Geoffrey Stretton ,  Kenneth Franklin Udall

    IPC: B64D27/00 ,  B64D27/26

    CPC classification number: B64D27/26 ,  B64D2027/262 ,  B64D2027/266

    Abstract: An engine mount, for mounting the casing of an aircraft engine to the fuselage or wing of an aircraft, e.g. via a pylon, including first and second links having connector formations for connection to respective mounting and support formations on the engine casing and aircraft mounting structure. Each of the first and second links is typically connected by a pin between the mounting and support formations. Each link has a further connector formation arranged such that the connector formation of the first link is offset from the connector formation of the second link. The connector formations are joined by an intermediate link. The mount allows lateral forces and torque to be resolved in such a way as to substantially avoid lateral displacement of the engine away from a central plane. The intermediate link may also provide a failsafe catcher arrangement in the event that the first or second link fail.

    Engine installation
    7.
    发明授权
    Engine installation 有权
    发动机安装

    公开(公告)号：US09346551B2

    公开(公告)日：2016-05-24

    申请号：US14173394

    申请日：2014-02-05

    Applicant: ROLLS-ROYCE PLC

    Inventor： Richard Geoffrey Stretton

    IPC: B64D27/00 ,  B64D27/14 ,  B64D29/04

    CPC classification number: B64D27/14 ,  B64D29/04 ,  B64D35/00 ,  B64D2027/005 ,  Y02T50/44 ,  Y02T50/66

    Abstract: A fuselage mounted gas turbine engine installation the installation includes at least one propeller stage and a gas turbine core arranged in use to drive the propeller stage. The core is external to the fuselage and the rotational axes of the core and propeller stage are offset with respect to each other.

    Abstract translation: 机身安装的燃气涡轮发动机安装包括至少一个螺旋桨级和燃气轮机芯，其布置在使用中以驱动螺旋桨级。 芯体在机身外部，并且芯部和螺旋桨台的旋转轴线相对于彼此偏移。

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