公开(公告)号：US11873731B2

公开(公告)日：2024-01-16

申请号：US18114583

申请日：2023-02-27

Applicant: ROLLS-ROYCE plc

Inventor： Ian J. Bousfield ,  Duncan 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.

公开(公告)号：US20240426216A1

公开(公告)日：2024-12-26

申请号：US18825241

申请日：2024-09-05

Applicant: ROLLS-ROYCE plc

Inventor： Ian J. Bousfield ,  Duncan A. Macdougall

IPC: F01D5/14 ,  F02C7/05 ,  F02C7/36

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.

公开(公告)号：US12110804B2

公开(公告)日：2024-10-08

申请号：US18524490

申请日：2023-11-30

Applicant: ROLLS-ROYCE plc

Inventor： Ian J. Bousfield ,  Duncan 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.