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.