公开(公告)号：US20220333525A1

公开(公告)日：2022-10-20

申请号：US17747960

申请日：2022-05-18

Applicant: Rolls-Royce Corporation

Inventor： Mark E. Whitlock ,  Nathanael Cooper ,  Steven Mazur ,  Michael Nesteroff ,  Paul Melevage

IPC: F02C3/08 ,  F02C6/08 ,  F02C7/28

Abstract: A gas turbine engine includes a fan, a compressor, a combustor, and a turbine. The compressor compresses gases entering the gas turbine engine. The combustor receives the compressed gases from the compressor and mixes fuel with the compressed gases. The turbine receives the hot, high pressure combustion products created by the combustor by igniting the fuel mixed with the compressed gases. The turbine extracts mechanical work from the hot, high pressure combustion products to drive the fan and compressor.

公开(公告)号：US11525393B2

公开(公告)日：2022-12-13

申请号：US16824171

申请日：2020-03-19

Applicant: Rolls-Royce Corporation

Inventor： Mark E. Whitlock ,  Nathanael Cooper ,  Steven Mazur ,  Michael Nesteroff ,  Paul Melevage

IPC: F02C3/08 ,  F02C6/08 ,  F02C7/28 ,  F01D5/04 ,  F01D5/08

Abstract: A gas turbine engine includes a fan, a compressor, a combustor, and a turbine. The compressor compresses gases entering the gas turbine engine. The combustor receives the compressed gases from the compressor and mixes fuel with the compressed gases. The turbine receives the hot, high pressure combustion products created by the combustor by igniting the fuel mixed with the compressed gases. The turbine extracts mechanical work from the hot, high pressure combustion products to drive the fan and compressor.

公开(公告)号：US20250163821A1

公开(公告)日：2025-05-22

申请号：US18512681

申请日：2023-11-17

Applicant: Rolls-Royce Corporation

Inventor： Michael Nesteroff ,  Mark E. Whitlock ,  Nathanael Cooper ,  Jonathan Acker

IPC: F01D11/22

Abstract: A compressor assembly for a gas turbine engine comprising an outer case, a shroud arranged circumferentially around the axis to direct compressed air through an impeller, and an actuator coupled with the outer case and the shroud to vary the position of the shroud axially relative to the outer case. The actuator includes a mount arm, an actuator body, and a travel stop. The mount arm is coupled with the outer case. The actuator body is coupled with the mount arm and the shroud to control axial movement of the shroud relative to the outer case. The travel stop is coupled to the mount arm and extends away from the mound arm and is configured to limit a forward most axial position of the shroud relative to the outer case.

公开(公告)号：US20250163820A1

公开(公告)日：2025-05-22

申请号：US18512672

申请日：2023-11-17

Applicant: Rolls-Royce Corporation

Inventor： Michael Nesteroff ,  Mark E. Whitlock ,  Nathanael Cooper ,  Jonathan Acker

IPC: F01D17/12 ,  F01D9/04

Abstract: A compressor assembly for a gas turbine engine includes a shroud assembly, an outer case assembly, and a plurality of locating bolt assemblies. The shroud assembly extends circumferentially around the engine axis. The outer case assembly includes an outer case that extends circumferentially around the axis and a plurality of fasteners that couple the shroud assembly with the outer case. The plurality of locating bolt assemblies extend into the outer case and abut the shroud assembly at a predetermined axial location to axially locate the shroud assembly.

公开(公告)号：US12264685B1

公开(公告)日：2025-04-01

申请号：US18640404

申请日：2024-04-19

Applicant: Rolls-Royce North American Technologies Inc. ,  Rolls-Royce Corporation

Inventor： Kerry J. Lighty ,  Jonathan P. Acker ,  Douglas J. Kremer ,  Steven Mazur ,  Mark E. Whitlock

IPC: F04D27/02

Abstract: A bleed valve assembly includes a manifold coupled to a case of a compressor of a gas turbine engine to control a flow of bleed air exiting the compressor, a valve housing coupled with the manifold, a piston configured to move selectively relative to the valve housing and the manifold, and one or more shims located between the valve housing and the piston.

公开(公告)号：US20230374936A1

公开(公告)日：2023-11-23

申请号：US18225089

申请日：2023-07-21

Applicant: Rolls-Royce Corporation

Inventor： Mark E. Whitlock ,  Nathanael Cooper ,  Steven Mazur ,  Michael Nesteroff ,  Paul Melevage

IPC: F02C3/08 ,  F02C6/08 ,  F02C7/28 ,  F02C7/18

CPC classification number: F02C3/08 ,  F02C6/08 ,  F02C7/28 ,  F02C7/18 ,  F05D2220/3219 ,  F01D5/081

Abstract: A gas turbine engine includes a fan, a compressor, a combustor, and a turbine. The compressor compresses gases entering the gas turbine engine. The combustor receives the compressed gases from the compressor and mixes fuel with the compressed gases. The turbine receives the hot, high pressure combustion products created by the combustor by igniting the fuel mixed with the compressed gases. The turbine extracts mechanical work from the hot, high pressure combustion products to drive the fan and compressor.

公开(公告)号：US11746695B2

公开(公告)日：2023-09-05

申请号：US17747960

申请日：2022-05-18

Applicant: Rolls-Royce Corporation

Inventor： Mark E. Whitlock ,  Nathanael Cooper ,  Steven Mazur ,  Michael Nesteroff ,  Paul Melevage

IPC: F02C3/08 ,  F02C6/08 ,  F02C7/28 ,  F02C7/18 ,  F01D5/08

CPC classification number: F02C3/08 ,  F02C6/08 ,  F02C7/18 ,  F02C7/28 ,  F01D5/081 ,  F05D2220/3219

Abstract: A gas turbine engine includes a fan, a compressor, a combustor, and a turbine. The compressor compresses gases entering the gas turbine engine. The combustor receives the compressed gases from the compressor and mixes fuel with the compressed gases. The turbine receives the hot, high pressure combustion products created by the combustor by igniting the fuel mixed with the compressed gases. The turbine extracts mechanical work from the hot, high pressure combustion products to drive the fan and compressor.

公开(公告)号：US20210293180A1

公开(公告)日：2021-09-23

申请号：US16824171

申请日：2020-03-19

Applicant: Rolls-Royce Corporation

Inventor： Mark E. Whitlock ,  Nathanael Cooper ,  Steven Mazur ,  Michael Nesteroff ,  Paul Melevage

IPC: F02C3/08 ,  F01D5/04 ,  F02C6/08

Abstract: A gas turbine engine includes a fan, a compressor, a combustor, and a turbine. The compressor compresses gases entering the gas turbine engine. The combustor receives the compressed gases from the compressor and mixes fuel with the compressed gases. The turbine receives the hot, high pressure combustion products created by the combustor by igniting the fuel mixed with the compressed gases. The turbine extracts mechanical work from the hot, high pressure combustion products to drive the fan and compressor.

公开(公告)号：US20170342847A1

公开(公告)日：2017-11-30

申请号：US15165282

申请日：2016-05-26

Applicant: Rolls-Royce Corporation

Inventor： Steven A. Mazur ,  Mark E. Whitlock

IPC: F01D9/04 ,  F01D25/24 ,  F02C7/04

CPC classification number: F02C7/04 ,  F04D29/441 ,  F04D29/444 ,  F05D2230/237 ,  F05D2230/60 ,  F05D2240/123 ,  F05D2240/124 ,  F05D2250/52 ,  F05D2250/712

Abstract: A radial diffuser and method for manufacturing a radial diffuser is provided, where the diffuser includes a vane positioned between a hub and a case. The hub includes a surface. The vane projects from the surface of the hub and is wedge-shaped. The vane includes a leading end extending toward a radial inner edge of the hub, a trailing end extending toward a radial outer edge of the hub, an upper surface, first and second sides extending longitudinally along the vane, and a middle region disposed between the hub and the upper surface. The vane at the upper surface has a thickness defined by a first wedge angle at the upper surface. The vane at the middle region has a thickness defined by a second wedge angle at the middle region. The second wedge angle is smaller than the first wedge angle.