公开(公告)号：US20180252113A1

公开(公告)日：2018-09-06

申请号：US15907538

申请日：2018-02-28

Applicant: ROLLS-ROYCE plc

Inventor： Richard NORTHALL ,  Anthony J. RAE ,  Michael S. KRAUTHEIM ,  Alastair D. WALKER ,  Jonathan F. CARROTTE ,  Ian MARIAH

IPC: F01D9/04 ,  F01D5/14

Abstract: An annular array of turning vanes 200 is provided in a duct 100 of a gas turbine engine 10. The annular array of turning vanes 200 comprises aerodynamic vanes 220 and strut-vanes 240. The strut-vanes 240 have greater chord length and extend further axially downstream than the aerodynamic vanes 220. The leading edge of the strut-vanes 240 is upstream of the trailing edge of the aerodynamic vanes 220. The strut-vanes provide flow turning. The space to chord ratio of the aerodynamic vanes that are closest to the suction surface of a strut-vane is higher than the space to chord ratio of aerodynamic vanes that are closest to a pressure surface of the strut-vane. The arrangement allows the duct 100 to be axially short.

公开(公告)号：US20170138364A1

公开(公告)日：2017-05-18

申请号：US15335765

申请日：2016-10-27

Applicant: ROLLS-ROYCE plc

Inventor： Kiran S. AUCHOYBUR ,  Robert J. MILLER ,  Christopher R. HALL ,  Anthony J. RAE

IPC: F04D19/02 ,  F04D29/52 ,  F04D29/54 ,  F04D29/32

CPC classification number: F04D19/02 ,  F01D5/141 ,  F04D29/321 ,  F04D29/324 ,  F04D29/522 ,  F04D29/542 ,  F04D29/544 ,  F05D2240/122 ,  F05D2240/304 ,  F05D2250/38 ,  F05D2250/70 ,  Y02T50/673

Abstract: A multistage compressor for a gas turbine engine, the compressor comprising a plurality of compressor stages, each compressor stage comprising in axial flow series a row of rotor blades and a row of stator vanes. A radially inner end of the rotor blades are connected to a hub. A casing circumscribes the rotor blades and the stator vanes. The rotor blades and the stator vanes each have an aerofoil portion. Each of the aerofoil portions of the rotor blades and/or the stator vanes of one or more stages of the compressor are profiled in a spanwise direction such that the aerofoil portion has a trailing edge that is angled more towards the axial direction in a region proximal to the casing and hub than in a mid-region.

公开(公告)号：US20180252231A1

公开(公告)日：2018-09-06

申请号：US15907531

申请日：2018-02-28

Applicant: ROLLS-ROYCE plc

Inventor： Richard NORTHALL ,  Anthony J. RAE ,  Michael S. KRAUTHEIM ,  Alastair D. WALKER ,  Jonathan F. CARROTTE ,  Ian MARIAH

IPC: F04D29/54 ,  F02C3/06

Abstract: An annular array of turning vanes 200 is provided in a duct 100 of a gas turbine engine 10. The annular array of turning vanes 200 comprises aerodynamic vanes 220 and strut-vanes 240. The strut-vanes 240 have greater chord length and extend further axially downstream than the aerodynamic vanes 220. The leading edge of the strut-vanes 240 is upstream of the trailing edge of the aerodynamic vanes 220. The strut-vanes provide flow turning. The arrangement allows the duct 100 to be axially short.