公开(公告)号：US09771873B2

公开(公告)日：2017-09-26

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: F02C9/18 ,  F02K3/06 ,  F02K3/115 ,  F02C7/18 ,  F02C7/14 ,  F01D9/06 ,  F01D9/02 ,  F01D25/24 ,  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 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.

公开(公告)号：US10240536B2

公开(公告)日：2019-03-26

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 ,  F01D9/02 ,  F01D25/24 ,  F02K3/06 ,  F01D9/06 ,  F02C7/14 ,  F02K3/115

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.

公开(公告)号：US09885285B2

公开(公告)日：2018-02-06

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 centerline of the engine.

公开(公告)号：US08985507B2

公开(公告)日：2015-03-24

申请号：US13761475

申请日：2013-02-07

Applicant: Rolls-Royce PLC

Inventor： Angus Roy Smith ,  Dimitris Arzoglou

IPC: B64D33/02 ,  F02C7/04 ,  F02K3/06 ,  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 neighboring 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用于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。