公开(公告)号：US20230228196A1

公开(公告)日：2023-07-20

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 ,  F02C7/05 ,  F02C7/36 ,  F05D2220/32 ,  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：US20230045400A1

公开(公告)日：2023-02-09

申请号：US17969826

申请日：2022-10-20

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：US20220372886A1

公开(公告)日：2022-11-24

申请号：US17663600

申请日：2022-05-16

Applicant: ROLLS-ROYCE plc

Inventor： Duncan A. MACDOUGALL ,  Jaime TERRON FRAILE

IPC: F01D9/04 ,  F01D5/18 ,  F01D21/04

Abstract: A nozzle guide vane for a gas turbine engine having a combined side wall thickness value which varies within a cavity region so as to provide a point with a maximum value of combined side wall thickness, which is advantageous for capturing debris travelling through the engine core.

公开(公告)号：US20210285379A1

公开(公告)日：2021-09-16

申请号：US17333631

申请日：2021-05-28

Applicant: ROLLS-ROYCE PLC

Inventor： Ian J. BOUSFIELD ,  Duncan A. MACDOUGALL

IPC: F02C7/30 ,  F02C3/06 ,  F01D25/02 ,  F01D5/14

Abstract: A core duct assembly for a gas turbine engine includes a core duct including an outer and an inner wall, the outer wall having an interior surface; a gas flow path member extending across the gas flow path at least partly between the inner and outer walls, the rotor blade having a radial span extending from a blade platform to a blade tip, wherein an upstream wall axis is defined as an axis tangential to a point on a first portion of the interior surface of the outer wall of the core duct extending downstream from the gas flow path member, the upstream wall axis lying in a longitudinal plane of the gas turbine engine containing the rotational axis of the engine, and wherein the upstream wall axis intersects the rotor blade at a point spaced radially inward from the blade tip of the rotor blade.

公开(公告)号：US20200291862A1

公开(公告)日：2020-09-17

申请号：US16437283

申请日：2019-06-11

Applicant: ROLLS-ROYCE plc

Inventor： Ian J. BOUSFIELD ,  Duncan A. MACDOUGALL

IPC: F02C7/30 ,  F02C3/06

Abstract: A core duct assembly for a gas turbine engine, the core duct assembly including: a core duct including an outer and an inner wall, the outer wall having an interior surface; a gas flow path member extending across the gas flow path at least partly between the inner and outer walls, the rotor blade having a radial span extending from a blade platform to a blade tip, wherein an upstream wall axis is defined as an axis tangential to a point on a first portion of the interior surface of the outer wall of the core duct extending downstream from the gas flow path member, the upstream wall axis lying in a longitudinal plane of the gas turbine engine containing the rotational axis of the engine, and wherein the upstream wall axis intersects the rotor blade at a point spaced radially inward from the blade tip of the rotor blade.

公开(公告)号：US20230314249A1

公开(公告)日：2023-10-05

申请号：US18183999

申请日：2023-03-15

Applicant: ROLLS-ROYCE plc

Inventor： Zhen ZHOU ,  Duncan A. MACDOUGALL ,  Julian M. REED

IPC: G01L5/1627 ,  G01L1/22

CPC classification number: G01L5/1627 ,  G01L1/2218 ,  G01L1/2287

Abstract: A system and a method of testing a specimen. The system includes an endcap, a plurality of bars, a plurality of strain gauges, and a gas gun. The endcap includes a first surface and a second surface opposite to the first surface. The first surface is curved. Each bar is disposed in contact with the second surface of the endcap and extends along a longitudinal axis. Each strain gauge is disposed on a surface of a corresponding bar from the plurality of bars. At least one strain gauge is disposed on the surface of each bar. The gas gun is configured to fire a specimen towards the first surface of the endcap such that the specimen impacts the first surface at an oblique angle relative to the longitudinal axis.

公开(公告)号：US20230220780A1

公开(公告)日：2023-07-13

申请号：US18122807

申请日：2023-03-17

Applicant: ROLLS-ROYCE plc

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

IPC: F01D17/16 ,  F01D9/04 ,  F02C7/042

CPC classification number: F01D17/162 ,  F01D9/04 ,  F02C7/042 ,  F05D2220/323 ,  F05D2240/12

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：US20200271012A1

公开(公告)日：2020-08-27

申请号：US16437501

申请日：2019-06-11

Applicant: ROLLS-ROYCE plc

Inventor： Ian J. BOUSFIELD ,  Duncan A. MACDOUGALL

IPC: F01D25/02 ,  F01D5/14

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 edges, 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 the ratio of a maximum leading edge radius of curvature of the first rotor blades to a minimum leading edge radius of curvature of the first rotor blades is included between 2.2 and 3.5.