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：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：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.