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：US20160130959A1

公开(公告)日：2016-05-12

申请号：US14881962

申请日：2015-10-13

Applicant: ROLLS-ROYCE PLC

Inventor： Stephane Michel Marcel BARALON

IPC: F01D9/04 ,  F01D25/24 ,  F01D5/02

CPC classification number: F01D9/041 ,  F01D5/02 ,  F01D9/02 ,  F01D25/06 ,  F01D25/24 ,  F02K3/04 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2240/12 ,  F05D2250/14 ,  F05D2250/71 ,  F05D2260/96

Abstract: A gas turbine engine comprising in axial flow series: a fan having a fan rotor; a series passages defined between adjacent outlet guide vanes for guiding flow from the fan; and a bifurcation. The gas turbine engine further comprises a substantially annular fluid passageway extending from the fan to the bifurcation, the outlet guide vanes being positioned within the passageway. The passageway includes a profiled region. The profiled region includes a first circumferential portion positioned adjacent a second circumferential portion, the first circumferential portion having a first average radial thickness and a second circumferential portion having a second average radial thickness, the first average radial thickness being smaller than the second average radial thickness, wherein the first circumferential portion is positioned in a region corresponding to a circumferential position of the bifurcation, and wherein the profiled region is at an axial position corresponding to the axial position of the outlet guide vanes and the first circumferential portion extends continuously over two or more of the passages.

Abstract translation: 一种燃气涡轮发动机，包括轴向流动系列：具有风扇转子的风扇; 在相邻出口导向叶片之间限定的用于引导来自风扇的流动的串联通道; 和分岔。 燃气涡轮发动机还包括从风扇延伸到分叉的基本上环形的流体通道，出口导叶定位在通道内。 通道包括一个形状区域。 成型区域包括邻近第二周向部分定位的第一周向部分，第一周向部分具有第一平均径向厚度和具有第二平均径向厚度的第二周向部分，第一平均径向厚度小于第二平均径向厚度 ，其中所述第一周向部分位于对应于所述分叉的圆周位置的区域中，并且其中所述成型区域处于与所述出口导叶的轴向位置对应的轴向位置，并且所述第一周向部分连续地延伸超过两个或 更多的段落。

公开(公告)号：US20160130961A1

公开(公告)日：2016-05-12

申请号：US14881965

申请日：2015-10-13

Applicant: ROLLS-ROYCE PLC

Inventor： Stephane Michel Marcel BARALON

IPC: F01D9/06 ,  F01D25/24 ,  F01D17/10 ,  F01D5/02 ,  F01D9/04

CPC classification number: F01D9/065 ,  F01D5/02 ,  F01D9/02 ,  F01D9/041 ,  F01D17/105 ,  F01D25/06 ,  F01D25/24 ,  F02K3/04 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2240/12 ,  F05D2240/20 ,  F05D2250/14 ,  F05D2250/71 ,  F05D2260/96

Abstract: A gas turbine engine includes in axial flow series a fan rotor, a series of outlet guide vanes for guiding flow from the fan rotor; and a bifurcation. The gas turbine engine further includes a substantially annular fluid passageway extending from fan to the bifurcation, the outlet guide vanes being positioned within the passageway. The passageway includes a profiled region positioned upstream of the bifurcation, the profiled region including a first circumferential portion positioned adjacent a second circumferential portion, the first circumferential portion having a first average radial thickness and a second circumferential portion having a second average radial thickness, the first average radial thickness being smaller than second average radial thickness. The profiled region of the passageway is configured to modify the flow through the passageway so as to improve uniformity of a static pressure field from immediately upstream of the bifurcation to just downstream of the fan rotor.

Abstract translation: 燃气涡轮发动机包括轴流式系列的风扇转子，用于引导来自风扇转子的流的一系列出口导向叶片; 和分岔。 燃气涡轮发动机还包括从风扇延伸到分叉的大致环形的流体通道，出口导向叶片位于通道内。 所述通道包括位于所述分叉的上游的成型区域，所述成型区域包括邻近第二周向部分定位的第一周向部分，所述第一周向部分具有第一平均径向厚度和具有第二平均径向厚度的第二周向部分， 第一平均径向厚度小于第二平均径向厚度。 通道的成型区域被构造成改变通过通道的流动，以便改善静态压​​力场从分支的上游到风扇转子正下游的均匀性。

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。