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：US20230133728A1

公开(公告)日：2023-05-04

申请号：US17958996

申请日：2022-10-03

Applicant: ROLLS-ROYCE plc

Inventor： Duncan A MACDOUGALL ,  Julian M REED ,  Sophoclis PATSIAS ,  Antonio PELLEGRINO ,  Clive R SIVIOUR ,  Daniel EAKINS ,  Yuan XU ,  Junyi ZHOU

IPC: G01N3/30 ,  G01N3/02

Abstract: A system for measuring loading on a test specimen. The system includes the test specimen arranged between a first loading bar and a second loading bar. The system further includes a first loading unit and a second loading unit configured to apply a first load and a second load to the first and second loading bars, respectively. The system further includes a first clamp and a second clamp configured to hold the first and second loading bars against the first and second loads, respectively. The system further includes a clamp actuating unit configured to selectively release at least the first clamp. The clamp actuating unit further includes a controller configured to electrically actuate at least one first electromechanical transducer from a retained state to a released state to release the first clamp, such that the first loading bar applies a first loading wave to the test specimen.

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.

公开(公告)号：US20220162953A1

公开(公告)日：2022-05-26

申请号：US17514977

申请日：2021-10-29

Applicant: ROLLS-ROYCE plc

Inventor： Geoffrey B JONES ,  Edward J SPALTON ,  Duncan A MACDOUGALL

IPC: F01D9/04

Abstract: A gas turbine engine includes: a fan rotating about an engine main axis; a core duct; an engine core; an Engine Section Stator (ESS) including a plurality of ESS vanes and arranged in the core duct downstream of the fan; and a plurality of variable inlet guide vanes (VIGV) adapted to rotate about a pivot axis and arranged in the core duct downstream of the ESS. The VIGV vanes are arranged angularly rotated with respect to the ESS vanes such that the VIGVs are shielded by the ESS, thereby protecting the VIGVs from icing and from ice shedding from the ESS vanes.

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.