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：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：US20160108811A1

公开(公告)日：2016-04-21

申请号：US14857083

申请日：2015-09-17

Applicant: ROLLS-ROYCE PLC

Inventor： Christopher Alan MOSLEY ,  Angus Roy SMITH ,  Christopher Thomas John SHEAF ,  John Richard WELLS

IPC: F02C7/04 ,  F02K3/06

CPC classification number: F02C7/04 ,  F02K3/06 ,  F05D2250/232

Abstract: A nacelle for a turbofan gas turbine engine is provided. An inner wall of the nacelle defines an air intake which directs air into the fan section of the engine. The intake has, in flow series, an intake lip, a throat and a diffuser. The diffuser has, in flow series, first and second flow conditioning sections over both of which the flow cross-sectional area of the diffuser increases with increasing downstream distance from the throat. In addition, over the second section the nacelle inner wall lies substantially on a surface of an oblique circular cone having an apex which is offset from the centreline of the engine.

Abstract translation: 提供了一种涡轮风扇燃气涡轮发动机的机舱。 机舱的内壁限定了将空气引导到发动机的风扇部分中的进气口。 进气口具有进气口，喉部和扩散器。 扩散器具有流动系列中的第一和第二流量调节部分，两者之间的扩散器的流动横截面积随着与喉部的下游距离的增加而增加。 此外，在第二部分上，机舱内壁基本上位于具有偏离发动机中心线的顶点的倾斜圆锥的表面上。

公开(公告)号：US20130199624A1

公开(公告)日：2013-08-08

申请号：US13761475

申请日：2013-02-07

Applicant: Rolls-Royce PLC

Inventor： Angus Roy SMITH ,  Dimitris ARZOGLOU

IPC: F02C7/04 ,  G06F17/50

CPC classification number: F02C7/04 ,  B64C7/02 ,  B64D29/00 ,  B64D33/02 ,  F02K3/06 ,  G06F17/50 ,  Y10T137/0536

Abstract: A method of designing a nacelle for a gas turbine engine includes defining an initial geometry for the nacelle, pivoting, at each of one or more positions on a highlight and in a plane of a respective longitudinal section, a front portion of a section of an intake lip lying in the respective longitudinal section about the highlight, and obtaining an altered geometry for the nacelle by adjusting surfaces of the intake neighbouring the pivoted front portion to smoothly blend the surfaces of the pivoted front portion to unadjusted surfaces of the intake further removed from the pivoted front portion.

Abstract translation: 设计用于燃气涡轮发动机的发动机的机舱的方法包括限定机舱的初始几何形状，在高亮部分的一个或多个位置和相应的纵向部分的平面中的每个位置上枢转， 入口唇缘围绕高亮部位于相应的纵向部分中，并且通过调节邻近枢转的前部的进气口的表面来获得改变的机舱几何形状，以将枢转的前部的表面平滑地混合到进一步从 枢转的前部。