公开(公告)号：US20190353180A1

公开(公告)日：2019-11-21

申请号：US16529404

申请日：2019-08-01

Applicant: Rolls-Royce Corporation

Inventor： Nathan Ottow ,  Johnathan Acker ,  Nate Cooper ,  Mark Whitlock ,  Michael Nesteroff

IPC: F04D29/42 ,  F04D27/02 ,  F01D11/22 ,  F04D29/16

Abstract: A system for controlling the clearance distance between an impeller blade tip of a centrifugal compressor and a radially inner surface of a segregated impeller shroud in a turbine engine. The system comprises a driving mechanism coupled to a portion of a segregated impeller shroud. The driving mechanism comprises a driving arm and threaded axial member configured to translate motion of an actuator ring into axially forward and aft motion of the portion of the segregated impeller shroud.

公开(公告)号：US10352329B2

公开(公告)日：2019-07-16

申请号：US15165404

申请日：2016-05-26

Applicant: Rolls-Royce Corporation

Inventor： Michael Nesteroff ,  Jonathan Acker ,  Nate Cooper ,  Nathan Ottow

IPC: F01D11/22 ,  F04D29/16 ,  F01D11/24 ,  F04D27/02 ,  F04D29/62 ,  F01D11/18 ,  F01D11/08 ,  F04D29/42

Abstract: A system for controlling the clearance distance between an impeller blade tip of a centrifugal compressor and a radially inner surface of an impeller shroud in a turbine engine. The system comprises a thermal driver coupled between the impeller shroud and engine casing by hinged linkages. The thermal driver includes an annular ring and annular seal which together define thermal driver cavity. Relatively warm or relatively cool air supplied to the thermal driver cavity cause expansion and contraction, respectively, of the annular ring which is translated by linkages into axially forward and aft motion, respectively.

公开(公告)号：US20170342994A1

公开(公告)日：2017-11-30

申请号：US15165404

申请日：2016-05-26

Applicant: Rolls-Royce Corporation

Inventor： Michael Nesteroff ,  Jonathan Acker ,  Nate Cooper ,  Nathan Ottow

IPC: F04D27/00 ,  F04D29/42 ,  F04D29/16 ,  F04D29/28

CPC classification number: F04D29/162 ,  F01D11/08 ,  F01D11/18 ,  F01D11/22 ,  F01D11/24 ,  F04D27/0246 ,  F04D29/4206 ,  F04D29/622 ,  F04D29/624

Abstract: A system for controlling the clearance distance between an impeller blade tip of a centrifugal compressor and a radially inner surface of an impeller shroud in a turbine engine. The system comprises a thermal driver coupled between the impeller shroud and engine casing by hinged linkages. The thermal driver includes an annular ring and annular seal which together define thermal driver cavity. Relatively warm or relatively cool air supplied to the thermal driver cavity cause expansion and contraction, respectively, of the annular ring which is translated by linkages into axially forward and aft motion, respectively.

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：US11002284B2

公开(公告)日：2021-05-11

申请号：US16433089

申请日：2019-06-06

Applicant: Rolls-Royce Corporation

Inventor： Michael Nesteroff ,  Jonathan Acker ,  Nate Cooper ,  Nathan Ottow

IPC: F04D29/16 ,  F01D11/24 ,  F04D27/02 ,  F04D29/62 ,  F01D11/18 ,  F01D11/08 ,  F04D29/42 ,  F01D11/22

Abstract: A system for controlling the clearance distance between an impeller blade tip of a centrifugal compressor and a radially inner surface of an impeller shroud in a turbine engine. The system comprises a thermal driver coupled between the impeller shroud and engine casing by hinged linkages. The thermal driver includes an annular ring and annular seal which together define thermal driver cavity. Relatively warm or relatively cool air supplied to the thermal driver cavity cause expansion and contraction, respectively, of the annular ring which is translated by linkages into axially forward and aft motion, respectively.

公开(公告)号：US10731660B2

公开(公告)日：2020-08-04

申请号：US16104671

申请日：2018-08-17

Applicant: Rolls-Royce Corporation

Inventor： Michael Nesteroff ,  Jonathan Acker ,  Albert Moncada ,  David Templin

IPC: F04D29/44 ,  F01D9/04

Abstract: According to some aspects of the present disclosure, a diffuser for a centrifugal compressor is provided. The diffuser may comprise an outerband casing and an innerband casing. The outerband casing may comprise an annular flowpath boundary member that has a flowpath boundary surface. The flowpath boundary member may define a plurality of vane-receiving pockets spaced about a circumference of the member. The innerband casing may comprise an annular flowpath boundary member that has a flowpath boundary surface. The flowpath boundary member may comprise a plurality of vanes spaced about a circumference of the member. Each of said plurality of vanes may comprise a vane body that extends from the flowpath boundary surface, a platform head that has a lateral dimension normal to the length of the vane body greater than the lateral dimension of the vane body, and a fillet between the platform head and the vane body. The innerband casing may be positioned so that the platform head of each of the plurality of vanes is received in a respective vane-receiving pocket defined by the flowpath boundary member of the outerband casing. When received, the fillet of each of the plurality of vanes may be adjacent the flowpath boundary surface of the flowpath boundary member of said outerband casing. The flowpath boundary surfaces of each of said casings and said vanes define a fluid flowpath in said diffuser.

公开(公告)号：US10458429B2

公开(公告)日：2019-10-29

申请号：US15234601

申请日：2016-08-11

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

Inventor： Michael Nesteroff ,  Jonathan Acker ,  Jeffrey Crutchfield ,  Nate Cooper ,  Mark Whitlock ,  Nathan Ottow

IPC: F01D11/22 ,  F04D29/42 ,  F04D29/16 ,  F01D5/04 ,  F04D17/02 ,  F04D17/10 ,  F02C3/08 ,  F04D27/02 ,  F01D11/08 ,  F04D29/62 ,  F01D11/18

Abstract: A system for controlling the clearance distance between an impeller blade tip of a centrifugal compressor and a radially inner surface of an impeller shroud in a turbine engine. The system comprises a high pressure air source, an air piston mounted between an engine casing and the shroud and adapted to receive high pressure air from the high pressure air source, a mounting arm coupling the shroud and air piston, and a slidable coupling adapted to allow axial movement of the shroud and joining the shroud to an axial member.

公开(公告)号：US20170343001A1

公开(公告)日：2017-11-30

申请号：US15165468

申请日：2016-05-26

Applicant: Rolls-Royce Corporation

Inventor： Michael Nesteroff ,  Jonathan Acker ,  Jeffrey Crutchfield ,  Nathan Ottow

IPC: F04D29/16 ,  F04D29/28 ,  F04D29/42

CPC classification number: F04D29/162 ,  F04D29/284 ,  F04D29/4206 ,  F04D29/622 ,  F05D2220/32 ,  F05D2260/50

Abstract: A system for controlling the clearance distance between an impeller blade tip of a centrifugal compressor and a radially inner surface of an impeller shroud in a turbine engine. The system comprises a high pressure air source, an air piston mounted between an engine casing and the shroud and adapted to receive high pressure air from the high pressure air source, a mounting arm coupling the shroud and air piston, and a slidable coupling adapted to allow axial movement of the shroud and joining the shroud to an axial member.

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.