公开(公告)号：US11105338B2

公开(公告)日：2021-08-31

申请号：US16579011

申请日：2019-09-23

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

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

IPC: F04D29/42 ,  F04D29/16 ,  F01D5/04 ,  F01D11/22 ,  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：US10794219B2

公开(公告)日：2020-10-06

申请号：US15704898

申请日：2017-09-14

Applicant: Rolls-Royce Corporation

Inventor： Grace Aker ,  Alex Ertman ,  Jonathan Acker

IPC: F01D17/16 ,  F01D25/24 ,  F04D29/56

Abstract: The bearing surface between a thrust bushing and a boss/or face is increased with the addition of a ring or tab that extends radially into a casing bore configured to receive a bushing and cooperating spindle of a variable stator/guide vane. The addition of the ring adds additional bearing surface area without increasing the size of the vane penny, reducing spindle diameter or reducing the bushing bore diameter.

公开(公告)号：US20190383304A1

公开(公告)日：2019-12-19

申请号：US16007647

申请日：2018-06-13

Applicant: Rolls-Royce Corporation

Inventor： Grace Aker ,  Michael Nesteroff ,  Mark Eric Whitlock ,  Cassandra Cummings ,  Jonathan Acker ,  Younes Khamliche ,  Nathanael Cooper

IPC: F04D29/16 ,  F04D29/42 ,  F04D29/02

Abstract: A centrifugal impeller shroud assembly has a dynamically moveable impeller shroud for encasing a rotatable centrifugal impeller and resolving misalignment between the impeller shroud and the rotatable centrifugal impeller. The assembly comprises a static casing, an impeller shroud, a shroud arm, and a thermal member. The shroud arm is coupled between the casing and the impeller shroud. The thermal member is coupled to the impeller shroud and has a coefficient of thermal expansion (CTE) lower than the CTE of the shroud. The shroud arm comprises a flexible portion configured to flex responsive to a differential pressure across the shroud arm.

公开(公告)号：US20170342996A1

公开(公告)日：2017-11-30

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: F04D27/00 ,  F04D29/16 ,  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 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：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：US20170343334A1

公开(公告)日：2017-11-30

申请号：US15165153

申请日：2016-05-26

Applicant: Rolls-Royce Corporation

Inventor： Mark Whitlock ,  Jonathan Acker

IPC: G01B11/14

CPC classification number: G01B11/14

Abstract: A method of measuring the clearance between a rotating component and a static component in a rotating machine. The method comprises installing a rub pin on an interior surface of the static component, operating the rotating machine such that the rotating component impinges on the rub pin, securing the rotating machine, and inserting an optical device to visually ascertain the length of rub pin remaining. The method reduces the time and cost of clearance determinations by avoiding disassembly or the degree of disassembly of the rotating machine required to conduct a clearance determination.

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.

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.