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：US10215042B2

公开(公告)日：2019-02-26

申请号：US14881965

申请日：2015-10-13

Applicant: ROLLS-ROYCE PLC

Inventor： Stephane Michel Marcel Baralon

IPC: F01D9/06 ,  F01D9/02 ,  F01D25/06 ,  F02K3/04 ,  F01D5/02 ,  F01D9/04 ,  F01D17/10 ,  F01D25/24

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.

公开(公告)号：US10053997B2

公开(公告)日：2018-08-21

申请号：US14881962

申请日：2015-10-13

Applicant: ROLLS-ROYCE PLC

Inventor： Stephane Michel Marcel Baralon

IPC: F01D9/04 ,  F01D9/02 ,  F01D25/06 ,  F02K3/04 ,  F01D5/02 ,  F01D25/24

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.