公开(公告)号：US20240093610A1

公开(公告)日：2024-03-21

申请号：US18524490

申请日：2023-11-30

Applicant: ROLLS-ROYCE plc

Inventor： Ian J. BOUSFIELD ,  Ducan A. Macdougall

IPC: F01D5/14 ,  F02C7/05 ,  F02C7/36

CPC classification number: F01D5/141 ,  F01D5/142 ,  F02C7/05 ,  F02C7/36 ,  F05D2220/32 ,  F05D2240/24 ,  F05D2240/303 ,  F05D2260/94

Abstract: A gas turbine engine comprises a fan mounted to rotate about a main longitudinal axis; an engine core, comprising in axial flow series a compressor, a combustor, and a turbine coupled to the compressor through a shaft; a reduction gearbox that receives an input from the shaft and outputs drive to the fan so as to drive the fan at a lower rotational speed than the shaft; wherein the compressor comprises a first stage at an inlet and a second stage, downstream of the first stage, comprising respectively a first rotor with a row of first blades and a second rotor with a row of second blades, the first and second blades comprising respective leading edges, trailing edges and tips, and wherein the ratio of a maximum leading edge radius of the first blades to a maximum leading edge radius of the second blades is greater than 2.8.