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：US10962024B2

公开(公告)日：2021-03-30

申请号：US16452698

申请日：2019-06-26

Applicant: Rolls-Royce Corporation

Inventor： Michael Nesteroff ,  Mark Eric Whitlock ,  Nathanael Cooper

IPC: F04D29/16 ,  F04D29/62 ,  F01D11/22 ,  F04D29/42

Abstract: A compressor shroud assembly is disclosed comprising a dynamically moveable impeller shroud, a static compressor casing, an air piston mounted between said impeller shroud and said compressor casing, and a clearance control system. The air piston effects axial movement of said impeller shroud responsive to a supply of actuating air. The clearance control system regulates the pressure of actuating air in said air piston and comprises a supply conduit having a supply modulating valve and a discharge conduit having a blowoff check valve. The blowoff check valve is set to open at a predetermined differential pressure between pressure of the air piston and pressure of the supply of actuating air.

公开(公告)号：US20200056625A1

公开(公告)日：2020-02-20

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：US20190323514A1

公开(公告)日：2019-10-24

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 ,  F04D29/62 ,  F01D11/24 ,  F04D27/02

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：US10309409B2

公开(公告)日：2019-06-04

申请号：US15165468

申请日：2016-05-26

Applicant: Rolls-Royce Corporation

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

IPC: F04D29/42 ,  F04D29/16 ,  F04D29/28 ,  F04D29/62 ,  F01D11/22 ,  F01D11/08

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：US20170342995A1

公开(公告)日：2017-11-30

申请号：US15165728

申请日：2016-05-26

Applicant: Rolls-Royce Corporation

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

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

CPC classification number: F04D29/4206 ,  F01D11/08 ,  F01D11/22 ,  F01D25/24 ,  F04D27/0246 ,  F04D29/162 ,  F04D29/622 ,  F05D2220/3219 ,  F05D2240/11 ,  F05D2250/281 ,  F05D2260/57 ,  F05D2270/3013 ,  F05D2270/305

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.