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1. 发明授权

US09809317B2 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
申请人： ROLLS-ROYCE PLC
发明人： Richard Geoffrey Stretton , Kenneth Franklin Udall
IPC分类号： B64D27/26 , F02C7/20 , B64D27/10
CPC分类号： B64D27/26 , B64D27/10 , B64D2027/262 , F02C7/20 , F05D2220/325 , F05D2250/11
摘要： 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.

2. 发明授权

US09970313B2 Unison ring assembly 有权
公开(公告)号：US09970313B2
公开(公告)日：2018-05-15
申请号：US14716199
申请日：2015-05-19
申请人： ROLLS-ROYCE PLC
发明人： David Michael Beaven , Kenneth John Mackie , Richard Geoffrey Stretton
IPC分类号： F01D17/10 , F01D15/02 , B64C11/30
CPC分类号： F01D17/10 , B64C11/306 , F01D15/02 , F05D2220/36 , F05D2260/79
摘要： A unison ring assembly comprises a backing plate, and a plurality of pocket-forming portions. The backing plate is formed as an annular disc, with the annular disc being planar in a radial plane of the unison ring assembly. The plurality of pocket-forming portions are equi-spaced circumferentially around the axis of the unison ring assembly, and each of the plurality of pocket-forming portions is attached to the backing plate to form a corresponding radially extending pocket.

3. 发明授权

US10240536B2 Fluid system 有权
公开(公告)号：US10240536B2
公开(公告)日：2019-03-26
申请号：US14695918
申请日：2015-04-24
申请人： ROLLS-ROYCE PLC
发明人： Adam MacGregor Bagnall , Peter Beecroft , Richard Geoffrey Stretton , Philip Geoffrey Woodrow , Stephane Michel Marcel Baralon , Angus Roy Smith
IPC分类号： F02C9/18 , F02C7/18 , F02C6/08 , F01D9/02 , F01D25/24 , F02K3/06 , F01D9/06 , F02C7/14 , F02K3/115
摘要： A gas turbine engine is disclosed including a bifurcation fairing located in a bypass duct of the gas turbine engine and traversing the radial extent of the bypass duct. The bifurcation fairing has a delivery conduit inlet leading to a delivery conduit extending inside the bifurcation fairing, the delivery conduit being arranged in use for delivery of bypass air to one or more components of the gas turbine engine. A diverter conduit has a diverter conduit inlet from the delivery conduit upstream of the delivery conduit reaching the one or more components of the gas turbine engine. The diverter conduit has an outlet to a location other than the one or more components of the gas turbine engine.

4. 发明授权

US09387923B2 Gas turbine engine 有权
标题翻译：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
申请人： ROLLS-ROYCE PLC
发明人： Richard Geoffrey Stretton , Nicholas Howarth
IPC分类号： B64C11/00 , F02C3/067
CPC分类号： 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
摘要： 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).
摘要翻译：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）。

5. 发明授权

US09771873B2 Bifurcation fairing 有权
公开(公告)号：US09771873B2
公开(公告)日：2017-09-26
申请号：US14705550
申请日：2015-05-06
申请人： ROLLS-ROYCE PLC
发明人： Peter Beecroft , Richard Geoffrey Stretton , Philip Geoffrey Woodrow , Stephane Michel Marcel Baralon , Angus Roy Smith
IPC分类号： F02C9/18 , F02K3/06 , F02K3/115 , F02C7/18 , F02C7/14 , F01D9/06 , F01D9/02 , F01D25/24 , F02C6/08
CPC分类号： F02C9/18 , F01D9/02 , F01D9/065 , F01D25/24 , F02C6/08 , F02C7/14 , F02C7/18 , F02C7/185 , F02K3/06 , F02K3/115 , Y02T50/675
摘要： A gas turbine engine including an outlet guide vane and a bifurcation fairing is disclosed. The outlet guide vane is located in a bypass duct of the gas turbine engine downstream of a fan and is of aerofoil form. The bifurcation fairing traverses the radial extent of the bypass duct and has an upstream end that blends into a trailing edge of the outlet guide vane. The bifurcation fairing includes a scoop protruding outwards from its side corresponding to a pressure side of the upstream outlet guide vane. The scoop includes a forward facing inlet leading to a delivery conduit extending inside the bifurcation fairing for delivery in use of bypass air to one or more components of the gas turbine engine.

6. 发明授权

US09701412B2 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
申请人： ROLLS-ROYCE PLC
发明人： Richard Geoffrey Stretton , Kenneth Franklin Udall
IPC分类号： B64D27/00 , B64D27/26
CPC分类号： B64D27/26 , B64D2027/262 , B64D2027/266
摘要： 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.

7. 发明授权

US09346551B2 Engine installation 有权
标题翻译：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
申请人： ROLLS-ROYCE PLC
发明人： Richard Geoffrey Stretton
IPC分类号： B64D27/00 , B64D27/14 , B64D29/04
CPC分类号： B64D27/14 , B64D29/04 , B64D35/00 , B64D2027/005 , Y02T50/44 , Y02T50/66
摘要： 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.
摘要翻译：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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