Ray F Bowman

US Patent:

8079221, Dec 20, 2011

Filed:

Jan 11, 2011

Appl. No.:

13/004633

Inventors:

Ray F. Bowman - Carmel IN, US
Joseph A. Jaeger - Greenwood IN, US
Phillip J. Steffen - Avon IN, US
Robert G. Kiser - Indianapolis IN, US

Assignee:

Rolls-Royce Corporation - Indianapolis IN

International Classification:

F02C 9/00

US Classification:

60794

Abstract:

One embodiment of the present application is a gas turbine engine with a compressor that includes a variable geometry mechanism to vary working fluid flow area. A desired state of this mechanism is selected different than a current state to change the amount of flow area. The mechanism has a hysteresis band corresponding to a difference between increasing the flow area to reach the desired state and decreasing the flow area to reach the desired state. To control operation of the mechanism within this hysteresis band, a determination is made whether the desired state corresponds to a greater flow area or a lesser flow area relative to the current state.

US Patent:

20070084211, Apr 19, 2007

Filed:

Oct 18, 2005

Appl. No.:

11/253159

Inventors:

Ray Bowman - Carmel IN, US
Joseph Jaeger - Greenwood IN, US
Phillip Steffen - Avon IN, US
Robert Kiser - Indianapolis IN, US

International Classification:

F02C 9/20

US Classification:

060772000, 060794000

Abstract:

One embodiment of the present application is a gas turbine engine with a compressor that includes a variable geometry mechanism to vary working fluid flow area. A desired state of this mechanism is selected different than a current state to change the amount of flow area. The mechanism has a hysteresis band corresponding to a difference between increasing the flow area to reach the desired state and decreasing the flow area to reach the desired state. To control operation of the mechanism within this hysteresis band, a determination is made whether the desired state corresponds to a greater flow area or a lesser flow area relative to the current state.

US Patent:

20100162718, Jul 1, 2010

Filed:

Dec 22, 2009

Appl. No.:

12/645308

Inventors:

Ray F. Bowman - Carmel IN, US

International Classification:

F02C 9/00
F02C 6/04
G06F 19/00

US Classification:

60773, 60785, 701100

Abstract:

One embodiment according to the present invention is a unique system for gas turbine engine control. Other embodiments include unique apparatuses, systems, devices, and methods relating to gas turbine engines. Further embodiments, forms, objects, features, advantages, aspects, and benefits of the present invention shall become apparent from the following description and drawings.

US Patent:

20100162719, Jul 1, 2010

Filed:

Dec 23, 2009

Appl. No.:

12/645998

Inventors:

Ray F. Bowman - Carmel IN, US
Philip Ray Owen - Indianapolis IN, US

International Classification:

F02C 9/22
F01D 17/12

US Classification:

60773, 415148

Abstract:

A gas turbine engine is provided having a variety of forms and features. The gas turbine engine can include a compressor having movable vanes. In one form of operation the compressor can close down the vanes to a relatively low flow capacity position and the compressor can be operated at a higher speed, whereupon the vanes can be repositioned and the gas turbine engine operated at a different condition. The gas turbine engine can include a turbine having movable vanes. In one form of operation the turbine can change the vane positions to a relatively low torque position and the engine operated at a higher fuel flow condition, whereupon the vanes can be repositioned and the gas turbine engine operated at a different condition. The gas turbine engine can have a heater that adds heat to a flow stream, a motor that provides energy to a shaft, and an external load.

US Patent:

20100162720, Jul 1, 2010

Filed:

Dec 23, 2009

Appl. No.:

12/646018

Inventors:

Ray F. Bowman - Carmel IN, US
Philip Ray Owen - Indianapolis IN, US

International Classification:

F02C 9/00
F01D 7/02

US Classification:

60773, 415148

Abstract:

A gas turbine engine is provided having a variety of forms and features. The gas turbine engine can include a compressor having movable vanes. In one form of operation the compressor can close down the vanes to a relatively low flow capacity position and the compressor can be operated at a higher speed, whereupon the vanes can be repositioned and the gas turbine engine operated at a different condition. The gas turbine engine can include a turbine having movable vanes. In one form of operation the turbine can change the vane positions to a relatively low torque position and the engine operated at a higher fuel flow condition, whereupon the vanes can be repositioned and the gas turbine engine operated at a different condition. The gas turbine engine can have a heater that adds heat to a flow stream, a motor that provides energy to a shaft, and an external load.

US Patent:

20100164234, Jul 1, 2010

Filed:

Dec 23, 2009

Appl. No.:

12/646385

Inventors:

Ray F. Bowman - Carmel IN, US
Philip Ray Owen - Indianapolis IN, US

International Classification:

H02K 7/18
F02C 6/04
F02C 9/00
F01B 21/04

US Classification:

290 1 R, 60785, 60 3924, 60706

Abstract:

A gas turbine engine is provided having a variety of forms and features. The gas turbine engine can include a compressor having movable vanes. In one form of operation the compressor can close down the vanes to a relatively low flow capacity position and the compressor can be operated at a higher speed, whereupon the vanes can be repositioned and the gas turbine engine operated at a different condition. The gas turbine engine can include a turbine having movable vanes. In one form of operation the turbine can change the vane positions to a relatively low torque position and the engine operated at a higher fuel flow condition, whereupon the vanes can be repositioned and the gas turbine engine operated at a different condition. The gas turbine engine can have a heater that adds heat to a flow stream, a motor that provides energy to a shaft, and an external load.

US Patent:

20110154830, Jun 30, 2011

Filed:

Nov 22, 2010

Appl. No.:

12/951274

Inventors:

Ray F. Bowman - Carmel IN, US
Stanford Clemens - Westfield IN, US

International Classification:

F02C 6/04
F02C 9/00

US Classification:

60785, 60 3924

Abstract:

The present invention provides in one embodiment of the present invention a surge margin power recuperation system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for recuperating power from surge margin bleed air. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.

US Patent:

20110271687, Nov 10, 2011

Filed:

Dec 30, 2010

Appl. No.:

12/982449

Inventors:

Carl David Nordstrom - Avon IN, US
Ray F. Bowman - Carmel IN, US

International Classification:

F02C 6/04

US Classification:

60785

Abstract:

One embodiment of the present invention is a unique gas turbine engine with a bleed air powered auxiliary engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for bleed air powered auxiliary engines. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.