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。