Jonathan P Acker

US Patent:

20190383304, Dec 19, 2019

Filed:

Jun 13, 2018

Appl. No.:

16/007647

Inventors:

- Indianapolis IN, US
Michael Nesteroff - Indianapolis IN, US
Mark Eric Whitlock - Zionsville IN, US
Cassandra Cummings - Indianapolis IN, US
Jonathan Acker - Westfield IN, US
Younes Khamliche - Carmel IN, US
Nathanael Cooper - Avon IN, US

Assignee:

Rolls-Royce Corporation - Indianapolis IN

International Classification:

F04D 29/16
F04D 29/42
F04D 29/02

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.

US Patent:

20190323514, Oct 24, 2019

Filed:

Jun 6, 2019

Appl. No.:

16/433089

Inventors:

- Indianapolis IN, US
Jonathan Acker - Westfield IN, US
Nate Cooper - Avon IN, US
Nathan Ottow - Indianapolis IN, US

Assignee:

Rolls-Royce Corporation - Indianapolis IN

International Classification:

F04D 29/16
F04D 29/62
F01D 11/24
F04D 27/02

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.

US Patent:

20190078461, Mar 14, 2019

Filed:

Sep 14, 2017

Appl. No.:

15/704898

Inventors:

- Indianapolis IN, US
Alex Ertman - Indianapolis IN, US
Jonathan Acker - Westfield IN, US

Assignee:

Rolls-Royce Corporation - Indianapolis IN

International Classification:

F01D 17/16
F01D 25/24
F04D 29/56

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.

US Patent:

20180017078, Jan 18, 2018

Filed:

Jul 12, 2016

Appl. No.:

15/208229

Inventors:

- Indianapolis IN, US
Mark Whitlock - Zionsville IN, US
Jonathan Acker - Westfield IN, US
Nate Cooper - Avon IN, US

International Classification:

F04D 29/54
F04D 17/10
F02K 3/06
F04D 29/28
F04D 29/32
F04D 29/44
F04D 19/02

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.

US Patent:

20170342994, Nov 30, 2017

Filed:

May 26, 2016

Appl. No.:

15/165404

Inventors:

- Indianapolis IN, US
Jonathan Acker - Westfield IN, US
Nate Cooper - Avon IN, US
Nathan Ottow - Indianapolis IN, US

Assignee:

Rolls-Royce Corporation - Indianapolis IN

International Classification:

F04D 27/00
F04D 29/42
F04D 29/16
F04D 29/28

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.

US Patent:

20170342995, Nov 30, 2017

Filed:

May 26, 2016

Appl. No.:

15/165728

Inventors:

- Indianapolis IN, US
Jonathan Acker - Westfield IN, US
Nate Cooper - Avon IN, US
Mark Whitlock - Zionsville IN, US
Michael Nesteroff - Indianapolis IN, US

Assignee:

Rolls-Royce Corporation - Indianapolis IN

International Classification:

F04D 27/00
F04D 29/42
F04D 29/16
F04D 29/28

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.

US Patent:

20170343001, Nov 30, 2017

Filed:

May 26, 2016

Appl. No.:

15/165468

Inventors:

- Indianapolis IN, US
Jonathan Acker - Westfield IN, US
Jeffrey Crutchfield - Indianapolis IN, US
Nathan Ottow - Indianapolis IN, US

Assignee:

Rolls-Royce Corporation - Indianapolis IN

International Classification:

F04D 29/16
F04D 29/28
F04D 29/42

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.

US Patent:

20170343002, Nov 30, 2017

Filed:

May 26, 2016

Appl. No.:

15/165555

Inventors:

- Indianapolis IN, US
Jonathan Acker - Westfield IN, US
Nate Cooper - Avon IN, US

Assignee:

Rolls-Royce Corporation - Indianapolis IN

International Classification:

F04D 29/16
F04D 29/42
F04D 27/00
F04D 29/28

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.