公开(公告)号：US20210254501A1

公开(公告)日：2021-08-19

申请号：US17235234

申请日：2021-04-20

Applicant: ROLLS-ROYCE PLC

Inventor： Ian J BOUSFIELD ,  Duncan A MACDOUGALL

IPC: F01D25/02 ,  F01D5/14 ,  F04D29/32

Abstract: A gas turbine engine includes a fan mounted to rotate about a main longitudinal axis; an engine core, including a compressor, a combustor, and turbine coupled to the compressor through a shaft; and reduction gearbox; wherein the compressor includes a plurality of stages, each stage including a respective rotor and stator, a first stage of the plurality of stages being arranged at an inlet and including a first rotor with a plurality of blades; each blade extending chordwise from a leading edge to a trailing edge, and from root to tip for a span height, wherein 0% of the span height corresponds to the root and 100% of span height corresponds to tip; wherein a ratio of a leading edge radius of each of the plurality of first rotor blades at 0% span height to a minimum leading edge radius is comprised between 1 and 1.50.

公开(公告)号：US20210301763A1

公开(公告)日：2021-09-30

申请号：US17196393

申请日：2021-03-09

Applicant: ROLLS-ROYCE PLC

Inventor： Ian J BOUSFIELD ,  Michael O. HALES

IPC: F02K3/06 ,  F02C3/107 ,  F02C3/06 ,  F02C7/36

Abstract: A gas turbine engine including an engine core with high and low pressure compressors and high and low pressure turbines, the high pressure compressor and high pressure turbine being coupled by a high pressure shaft, and the low pressure compressor and low pressure turbine being coupled by a low pressure shaft, the engine further including a fan coupled to the low pressure shaft by a reduction gearbox. The high pressure compressor consists of 8 or 9 stages and has an average stage loading at cruise conditions of between 1.39 and 1.42, and the low and high pressure compressor together define an overall core pressure ratio at cruise conditions of between 40 and 60.

公开(公告)号：US20200347786A1

公开(公告)日：2020-11-05

申请号：US16813830

申请日：2020-03-10

Applicant: ROLLS-ROYCE PLC

Inventor： Ian J BOUSFIELD ,  Duncan A MACDOUGALL

IPC: F02C7/36 ,  F01D5/14

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：US20210301719A1

公开(公告)日：2021-09-30

申请号：US17196546

申请日：2021-03-09

Applicant: ROLLS-ROYCE PLC

Inventor： Ian J BOUSFIELD ,  Michael O HALES ,  Rory D STIEGER

IPC: F02C3/06 ,  F02C7/36

Abstract: A gas turbine engine including: a high pressure turbine, a low pressure turbine, a high pressure compressor coupled to the high pressure turbine by a high pressure shaft, a propulsor and a low pressure compressor coupled to the low pressure turbine via a low pressure shaft and a reduction gearbox; wherein the high pressure compressor defines an average stage pressure ratio at cruise conditions of between 1.25 and 1.35 and consists of 10 or 11 stages; and the high pressure compressor and low pressure compressor together define a core overall pressure ratio at cruise conditions of between 40:1 and 60:1.

公开(公告)号：US20210215103A1

公开(公告)日：2021-07-15

申请号：US17218617

申请日：2021-03-31

Applicant: ROLLS-ROYCE PLC

Inventor： Ian J BOUSFIELD ,  Duncan A MACDOUGALL

IPC: F02C7/36 ,  F01D5/14

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.