公开(公告)号：US10309410B2

公开(公告)日：2019-06-04

申请号：US15165555

申请日：2016-05-26

Applicant: Rolls-Royce Corporation

Inventor： Nathan Ottow ,  Jonathan Acker ,  Nate Cooper

IPC: F01D11/22 ,  F04D29/16 ,  F04D29/28 ,  F04D29/42 ,  F04D27/00 ,  F04D27/02 ,  F01D11/08 ,  F04D29/62

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 two-piece integral impeller shroud with a fixed inner member and a variable outer member. An actuator is coupled to an aft end of the variable outer member and imparts axially forward and aft motion on the aft end, causing deflection of the outer member.

公开(公告)号：US20190078461A1

公开(公告)日：2019-03-14

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

CPC classification number: F01D17/162 ,  F01D25/24 ,  F04D29/563 ,  F05D2230/10 ,  F05D2230/60 ,  F05D2240/12 ,  F05D2240/14 ,  F05D2240/50 ,  F05D2260/79

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：US20180017078A1

公开(公告)日：2018-01-18

申请号：US15208229

申请日：2016-07-12

Applicant: Rolls-Royce Corporation

Inventor： Steven Mazur ,  Mark Whitlock ,  Jonathan Acker ,  Nate Cooper

IPC: F04D29/54 ,  F04D17/10 ,  F02K3/06 ,  F04D29/28 ,  F04D29/32 ,  F04D29/44 ,  F04D19/02

CPC classification number: F04D29/545 ,  F01D9/045 ,  F02K3/06 ,  F04D17/10 ,  F04D19/02 ,  F04D29/284 ,  F04D29/321 ,  F04D29/444 ,  F05D2220/32 ,  F05D2240/128 ,  F05D2240/14 ,  F05D2240/30 ,  F05D2240/55

Abstract: An engine includes a compressor having a first compressor, a second compressor, and a static hub transition duct. The first compressor includes a rotatable portion and a static portion. The second compressor is disposed downstream of the first compressor and includes an inlet and a rotatable portion. The static hub transition duct includes an inner wall and an outer wall. The inner wall is secured to the static portion of the first compressor, and the inner wall and outer wall define a space that fluidically couples the first compressor and the inlet of the second compressor.

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：US20210062824A1

公开(公告)日：2021-03-04

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

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：US10704560B2

公开(公告)日：2020-07-07

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 ,  F04D29/02 ,  F04D29/42 ,  F01D11/20 ,  F01D11/08 ,  F04D29/62 ,  F01D11/24 ,  F01D11/16 ,  F01D11/18 ,  F01D11/22

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：US10408226B2

公开(公告)日：2019-09-10

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: F04D29/42 ,  F04D29/16 ,  F04D27/02 ,  F01D11/22 ,  F04D29/62 ,  F01D25/24 ,  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 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：US20190120250A1

公开(公告)日：2019-04-25

申请号：US15789456

申请日：2017-10-20

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

Inventor： Christopher Hall ,  Russell White ,  Jonathan Acker ,  Lyle Helvie

IPC: F04D29/56 ,  F04D29/64

CPC classification number: F04D29/563 ,  F04D29/644

Abstract: An apparatus and method of controlling the position of a variable vane in a compressor and a kit for adding such apparatus to the compressor are disclosed. The vane is coupled to a unison ring, a cam is secured to a torque tube, a cam follower is secured to the unison ring. The cam follower is secured such that a wall of the cam follower is in contact with the cam. Rotation of the torque tube causes movement of the cam, and movement of the cam moves the cam follower, thereby moving the unison ring and the variable vane coupled thereto.

公开(公告)号：US20170343002A1

公开(公告)日：2017-11-30

申请号：US15165555

申请日：2016-05-26

Applicant: Rolls-Royce Corporation

Inventor： Nathan Ottow ,  Jonathan Acker ,  Nate Cooper

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

CPC classification number: F04D29/162 ,  F04D27/002 ,  F04D27/0246 ,  F04D29/284 ,  F04D29/4206 ,  F05D2220/32 ,  F05D2240/11 ,  F05D2260/50 ,  F05D2260/57

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 two-piece integral impeller shroud with a fixed inner member and a variable outer member. An actuator is coupled to an aft end of the variable outer member and imparts axially forward and aft motion on the aft end, causing deflection of the outer member.

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.