Karl E Sheldon

US Patent:

7673459, Mar 9, 2010

Filed:

Apr 5, 2006

Appl. No.:

11/398108

Inventors:

Karl Edward Sheldon - Rexford NY, US
John Turco - West Chester OH, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F02C 6/06
F02C 7/00

US Classification:

60782, 60 39183, 60785, 62DIG 5, 454 76

Abstract:

A system for providing air to a compressor of an auxiliary gas turbine engine of an aircraft. A system turbine has an inlet adapted to receive compressed air from the aircraft. A system compressor is mechanically coupled to the system turbine and has an inlet adapted to receive atmospheric air. The outlets of the system turbine and the system compressor are fluidly connectable to the inlet of the compressor of the auxiliary gas turbine engine. A method includes providing compressed air from an aircraft to an inlet of a system turbine mechanically coupled to a system compressor. The method includes providing atmospheric air to an inlet of the system compressor. The method includes providing the inlet of the compressor of an auxiliary gas turbine engine with air from an outlet of the system turbine and with air from an outlet of the system compressor.

US Patent:

7707838, May 4, 2010

Filed:

Oct 31, 2006

Appl. No.:

11/590114

Inventors:

Karl Edward Sheldon - Rexford NY, US
Charles Erklin Seeley - Niskayuna NY, US
Ludwig Christian Haber - Rensselaer NY, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F02C 6/04

US Classification:

60785, 60 3983, 60802

Abstract:

An embodiment of the technology described herein is an auxiliary power unit assembly. The auxiliary power unit assembly includes an auxiliary power unit being installable in an aircraft having a cabin, a duct connecting the cabin and the auxiliary power unit, and an airflow management feature in the duct.

US Patent:

7721554, May 25, 2010

Filed:

Feb 2, 2006

Appl. No.:

11/345950

Inventors:

Chellappa Balan - Niskayuna NY, US
Karl Edward Sheldon - Rexford NY, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F02C 6/04

US Classification:

60785, 244 58, 60802

Abstract:

A non-aircraft-propelling auxiliary gas turbine engine installable in an aircraft having a cabin adapted to be pressurized. The auxiliary gas turbine engine includes an auxiliary-gas-turbine-engine compressor having an inlet, wherein the inlet is adapted to receive pressurized air from the cabin. A method for operating a non-aircraft-propelling auxiliary gas turbine engine of an aircraft includes providing pressurized air from the cabin of the aircraft to an inlet of a compressor of the auxiliary gas turbine engine. The method includes providing compressed air from the compressor to a combustor of the auxiliary gas turbine engine and includes providing combustion gases from the combustor to a turbine of the auxiliary gas turbine engine, wherein the turbine is mechanically coupled to the compressor.

US Patent:

8083467, Dec 27, 2011

Filed:

Jul 17, 2007

Appl. No.:

11/779147

Inventors:

Karl Edward Sheldon - Liberty Township OH, US
Michael Anthony Shockling - Clifton Park NY, US

Assignee:

General Electric Company - Niskayuna NY

International Classification:

F01D 21/02

US Classification:

415 30, 415202

Abstract:

An apparatus and method for controlling rotating bladed machinery by using a source of pressurized gas is disclosed. The source of pressurized gas, such as air, imparts braking torque on a turbomachinery component through the use of one or more impinging orifices or jets. The orientation of the jets is such that the transfer of momentum from the pressurized gas results in a force substantially opposite the direction of rotation of the turbomachinery component. This transfer of momentum from the pressurized gas allows for a controlling torque to be applied to the turbomachinery component without the need of mechanical and/or electrical devices applying torque to the rotating shaft.

US Patent:

20040191596, Sep 30, 2004

Filed:

Jun 13, 2002

Appl. No.:

10/064134

Inventors:

Michael Bowman - Niskayuna NY, US
Gautam Sinha - Clifton Park NY, US
Karl Sheldon - Clifton Park NY, US

Assignee:

General Electric Company - Niskayuna NY

International Classification:

H01M008/04

US Classification:

429/026000

Abstract:

In energy management system is provided for a power generating device having a working fluid intake in which the energy management system comprises an electrical dissipation device coupled to the power generating device and a dissipation device cooling system configured to direct a portion of a working fluid to the electrical dissipation device so as to provide thermal control to the electrical dissipation device.

US Patent:

20070220900, Sep 27, 2007

Filed:

Mar 27, 2006

Appl. No.:

11/389711

Inventors:

Michael Shockling - Clifton Park NY, US
Karl Sheldon - Rexford NY, US

International Classification:

F02C 6/00

US Classification:

060802000

Abstract:

A non-aircraft-propelling auxiliary gas turbine engine assembly includes an auxiliary gas turbine engine and a mixing damper. The auxiliary engine and the mixing damper are installable in an aircraft having at least one aircraft-propelling main gas turbine engine. The auxiliary engine includes a compressor having a compressor inlet. The mixing damper has first and second inlets and has an outlet. The outlet is fluidly connectable to the compressor inlet. The first and second inlets are adapted to receive first and second gas streams which have been compressed by at least one main engine. An aircraft component includes a mixing damper. A controller includes a program which instructs the controller to increase/decrease a first gas stream in response to increasing/decreasing electrical demands on an electric generator operatively connected to an auxiliary gas turbine engine of an aircraft.

US Patent:

20070240426, Oct 18, 2007

Filed:

Apr 12, 2006

Appl. No.:

11/402477

Inventors:

Herman Wiegman - Niskayuna NY, US
Karl Sheldon - Rexford NY, US
John Turco - West Chester OH, US
William Carlson - Liberty Township OH, US

International Classification:

F02C 9/00

US Classification:

060793000

Abstract:

A controller for operating a gas turbine engine, wherein the gas turbine engine is installable in an installation platform, wherein the gas turbine engine includes a compressor, a turbine, and a shaft connecting the turbine to the compressor. The controller includes a program which instructs the controller to run a computer dynamic model of the gas turbine engine, wherein the computer dynamic model has inputs including engine operating conditions and installation platform operating conditions. The controller also is programmed to calculate a dynamic limit on mechanical power extraction from the shaft based at least on the running of the computer dynamic model of the gas turbine engine. A method for operating a gas turbine engine installed in an aircraft includes running a computer dynamic model of the engine and calculating a dynamic limit on mechanical power extraction from a shaft of the engine based at least on the running of the model.

US Patent:

20090025393, Jan 29, 2009

Filed:

Oct 31, 2006

Appl. No.:

11/590041

Inventors:

Karl Edward Sheldon - Rexford NY, US
Charles Erklin Seeley - Niskayuna NY, US
Ludwig Christian Haber - Rensselaer NY, US
Trevor Howard Wood - Clifton Park NY, US
Jonathan Glenn Luedke - Clifton Park NY, US
Chingwei Michael Shieh - Mechanicville NY, US

International Classification:

F02C 7/24
F02K 1/06
F01N 1/24

US Classification:

60725, 181215, 181222

Abstract:

An embodiment of the technology described herein is an auxiliary power unit assembly. The auxiliary power unit assembly includes an auxiliary power unit being installable in an aircraft having a cabin, a duct connecting the cabin and the auxiliary power unit, and a noise reduction feature in the duct.