公开(公告)号：US20150330236A1

公开(公告)日：2015-11-19

申请号：US14705550

申请日：2015-05-06

Applicant: ROLLS-ROYCE PLC

Inventor： Peter BEECROFT ,  Richard Geoffrey STRETTON ,  Philip Geoffrey WOODROW ,  Stephane Michel Marcel BARALON ,  Angus Roy SMITH

IPC: F01D9/02 ,  F02C9/18 ,  F01D25/24

CPC classification number: F02C9/18 ,  F01D9/02 ,  F01D9/065 ,  F01D25/24 ,  F02C6/08 ,  F02C7/14 ,  F02C7/18 ,  F02C7/185 ,  F02K3/06 ,  F02K3/115 ,  Y02T50/675

Abstract: 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.

Abstract translation: 公开了一种包括出口导向叶片和分叉整流罩的燃气涡轮发动机。 出口导向叶片位于风扇下游的燃气涡轮发动机的旁通管道中，并且具有机翼形式。 分叉整流装置穿过旁路管道的径向范围，并具有与出口导叶的后缘相融合的上游端。 分叉整流罩包括从其对应于上游出口导流叶片的压力侧的一侧向外突出的勺子。 铲斗包括一个朝前的入口，通向延伸在分叉整流罩内部的输送导管，用于将旁路空气输送到燃气涡轮发动机的一个或多个部件。

公开(公告)号：US20150330309A1

公开(公告)日：2015-11-19

申请号：US14695918

申请日：2015-04-24

Applicant: ROLLS-ROYCE PLC

Inventor： Adam MacGregor BAGNALL ,  Peter BEECROFT ,  Richard Geoffrey STRETTON ,  Philip Geoffrey WOODROW ,  Stephane Michel Marcel BARALON ,  Angus Roy SMITH

IPC: F02C9/18 ,  F02C7/18 ,  F02C6/08

CPC classification number: F02C9/18 ,  F01D9/02 ,  F01D9/065 ,  F01D25/24 ,  F02C6/08 ,  F02C7/14 ,  F02C7/18 ,  F02C7/185 ,  F02K3/06 ,  F02K3/115 ,  Y02T50/675

Abstract: 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.

Abstract translation: 公开了一种燃气涡轮发动机，其包括位于燃气涡轮发动机的旁通管道中并横穿旁路管道的径向范围的分叉整流装置。 分叉整流罩具有通向在分叉整流装置内部延伸的输送导管的输送管道入口，输送导管布置成用于将旁路空气输送到燃气涡轮发动机的一个或多个部件。 分流管道具有从输送导管上游的输送管道到达燃气涡轮发动机的一个或多个部件的分流管道入口。 分流管道具有除了燃气涡轮发动机的一个或多个部件之外的位置的出口。

公开(公告)号：US20140017067A1

公开(公告)日：2014-01-16

申请号：US13914882

申请日：2013-06-11

Applicant: ROLLS-ROYCE PLC

Inventor： Richard Geoffrey STRETTON ,  Nicholas HOWARTH

IPC: B64C11/00

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）。

公开(公告)号：US20160167797A1

公开(公告)日：2016-06-16

申请号：US14543402

申请日：2014-11-17

Applicant: ROLLS-ROYCE PLC

Inventor： Richard Geoffrey STRETTON ,  Kenneth Franklin UDALL

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

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

Abstract: A mounting system is arranged in use for attaching a gas turbine engine to a pylon of an aircraft. The mounting system comprises a first frame of three elongate members arranged in a triangle. The first frame is arranged in use such that a core of the gas turbine engine is positioned extending through the area defined between the three elongate members. The first frame forms at least part of a load bearing connection between the pylon and gas turbine engine. The first frame consists of two portions, one corresponding to each side of the gas turbine engine when attached to the pylon. The triangle is symmetrical about a plane separating the two portions of the first frame.

Abstract translation: 安装系统被布置成用于将燃气涡轮发动机附接到飞机的塔架。 安装系统包括布置成三角形的三个细长构件的第一框架。 第一框架布置在使用中，使得燃气涡轮发动机的芯线定位成延伸穿过限定在三个细长构件之间的区域。 第一框架形成塔架和燃气涡轮发动机之间的承载连接的至少一部分。 第一框架由两部分组成，一部分与燃气涡轮发动机的每一侧对应，当连接到塔架上时。 三角形关于分开第一框架的两个部分的平面是对称的。

公开(公告)号：US20150361818A1

公开(公告)日：2015-12-17

申请号：US14716199

申请日：2015-05-19

Applicant: ROLLS-ROYCE PLC

Inventor： David Michael BEAVEN ,  Kenneth John MACKIE ,  Richard Geoffrey STRETTON

IPC: F01D17/10 ,  F01D15/02

CPC classification number: F01D17/10 ,  B64C11/306 ,  F01D15/02 ,  F05D2220/36 ,  F05D2260/79

Abstract: 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.

Abstract translation: 协调环组件包括背板和多个袋形成部分。 背板形成为环形盘，环形盘在协调环组件的径向平面中是平面的。 多个袋形成部分围绕协调环组件的轴线周向等间隔，并且多个袋形成部分中的每一个附接到背板以形成相应的径向延伸的袋。

公开(公告)号：US20150300254A1

公开(公告)日：2015-10-22

申请号：US14661704

申请日：2015-03-18

Applicant: ROLLS-ROYCE PLC

Inventor： Richard Geoffrey STRETTON

IPC: F02C7/04 ,  F02C7/05 ,  F02C7/18

CPC classification number: F02C7/04 ,  B64D2033/0226 ,  B64D2033/024 ,  B64D2033/0246 ,  F02C7/05 ,  F02C7/18 ,  F05D2220/32 ,  Y02T50/671

Abstract: An air intake for an open rotor engine including a propulsive blade array having a plurality of blades each having a gas washed surface extending radially outwardly relative to an axis or rotation from a root end to a tip. Intake has first and second circumferential walls extending about axis of rotation at a location downstream of propulsive blade array. First and second walls are spaced in a radial direction to define an annular passage with opening having a height dimension extending a portion of the way along propulsive blade array span. Intake further includes an annular lip arranged about axis of rotation at a radial distance such that lip bifurcates the annular passage at a height which separates a boundary layer flow portion of intake flow from a remainder of intake flow. Lip may define a collection scroll for foreign object debris and cooling air for the engine.

Abstract translation: 用于开式转子发动机的进气口，其包括具有多个叶片的推进叶片阵列，每个叶片各自具有相对于轴线径向向外延伸的气体洗涤表面或从根端到尖端的旋转。 进气口具有在推进式叶片阵列的下游位置处围绕旋转轴线延伸的第一和第二圆周壁。 第一和第二壁在径向方向上间隔开以限定具有开口的环形通道，其高度尺寸沿着推进式叶片阵列跨度延伸。 进气口还包括围绕旋转轴线在径向距离处布置的环形唇缘，使得唇部将进气流的边界层流动部分与进气流的剩余部分分开的高度分开环形通道。 唇部可以定义用于发动机的异物碎屑和冷却空气的收集卷轴。

公开(公告)号：US20150069176A1

公开(公告)日：2015-03-12

申请号：US14474760

申请日：2014-09-02

Applicant: ROLLS-ROYCE PLC

Inventor： Richard Geoffrey STRETTON ,  Kenneth Franklin UDALL

IPC: 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.

Abstract translation: 用于将飞机发动机的壳体安装到飞行器的机身或机翼上的发动机支架，例如 通过一个塔架，包括具有连接器结构的第一和第二连杆，用于连接到发动机壳体上的相应安装和支撑结构以及飞行器安装结构。 第一和第二连杆中的每一个通常通过销在安装和支撑结构之间连接。 每个连杆具有进一步的连接器形成，其布置成使得第一连杆的连接器形成从第二连杆的连接器形式偏移。 连接器结构通过中间链接连接。 该安装件允许以这样的方式解决横向力和扭矩，以便基本上避免发动机远离中心平面的横向位移。 在第一或第二链路故障的情况下，中间链路还可以提供故障保护捕获器装置。

公开(公告)号：US20140252159A1

公开(公告)日：2014-09-11

申请号：US14173394

申请日：2014-02-05

Applicant: ROLLS-ROYCE PLC

Inventor： Richard Geoffrey STRETTON

IPC: B64D27/14

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。