James Lewis Cooper
Engineers at Gregg Dr, Hamilton, OH

6672066, Jan 6, 2004

Apr 17, 2002

10/125301

Michael P. Wrubel - Westlake OH
Rex J. Harvey - Mentor OH
Peter Laing - Geneva OH
Robert T. Mains - Euclid OH
Barry W. Savel - Andover OH
Alfred A. Mancini - Cincinnati OH
James Neil Cooper - Hamilton OH

Parker-Hannifin Corporation - Cleveland OH

F02G 100

60740, 60 39281, 60742, 60746, 60772

A fuel injector nozzle for dispensing fuel in the combustion chamber of a gas turbine engine, includes an elongated, multi-layered, convoluted nozzle feed strip having an internal passage for directing fuel through the length of the strip from the inlet end to an outlet end; and a cylindrical, multi-layered fuel dispensing nozzle unitary with the feed strip and fluidly connected to the outlet end of the feed strip for dispensing the fuel. The multi-layered feed strip and nozzle allows complex porting of fuel circuits through the injector. The internal fluid passages through the feed strip and nozzle are formed by etching.

6389792, May 21, 2002

Apr 9, 2001

09/829384

Michael P. Hagle - Mason OH
Junhaur Jih - West Chester OH
James N. Cooper - Hamilton OH

General Electric Company - Schenectady NY

F02C 100

60 3902, 60753

A combustor liner has a stepped combustor liner surface and an overhang portion forming an air cooling slot. A contoured rear facing edge of the overhang portion reduces turbulence of combustion gas flow and reduces a combustor liner surface area exposed to combustion gases. A thermal barrier coating is also applied to the contoured rear facing edge, reducing heat flow into the overhang portion and hence reducing the operating temperature of the combustor liner. Thus, the amount of cooling air is reduced, which can reduce exhaust emissions increase engine performance and extend a working life of the combustor assembly.

6976363, Dec 20, 2005

Aug 11, 2003

10/638506

Marie Ann McMasters - Mason OH, US
James Neil Cooper - Hamilton OH, US
Michael Louis Vermeersch - Hamilton OH, US
Duane Douglas Thomsen - Loveland OH, US
Allen Michael Danis - Mason OH, US
Gregory Allen Cimmarusti - Mason OH, US

General Electric Company - Schenectady NY

F23R003/42

60800, 60748, 60752

A combustor dome assembly for a gas turbine engine having a longitudinal centerline axis extending therethrough includes: an annular dome plate having an inner portion, an outer portion, a forward surface, and a plurality of circumferentially spaced openings formed therein, wherein a radial section defined between each of the openings includes a cooling trough formed therein; and, a free floating swirler located upstream of the dome plate in substantial alignment with each of the openings in the dome plate, the swirler including a forward portion and an aft portion. The aft portion of each swirler is configured so as to permit air flow to the cooling trough during operation of the gas turbine engine. In particular, the swirler aft portion includes a substantially annular flange extending adjacent to the forward surface of the dome plate, wherein opposing portions of a circumference for the flange adjacent the radial sections of the dome plate are substantially linear.

5970716, Oct 26, 1999

Oct 2, 1997

8/942741

James M. Forrester - Springboro OH
Gregory A. Cimmarusti - Mason OH
David B. Legger - Mason OH
James N. Cooper - Hamilton OH
Robert J. Albers - Park Hills KY

General Electric Company - Cincinnati OH

F23R 350

60746

A double annular combustor having concentrically disposed inner and outer annular combustors including an inner dome having an inner portion and an outer portion, an outer dome having an inner portion and an outer portion, wherein the outer dome inner portion is connected to the inner dome outer portion, and a substantially annular centerbody disposed between the inner dome and the outer dome. The centerbody includes a plurality of structurally independent arcuate segments, wherein each centerbody segment is retained in position via an interference fit between a first flange of such centerbody extending downstream and a hook in the inner dome outer portion and/or via a clamping fit of a second flange of the centerbody extending upstream to a flange of the inner dome outer portion.

5321951, Jun 21, 1994

Jul 8, 1993

8/089058

Stephen W. Falls - Cincinnati OH
Eric J. Kress - Loveland OH
Joseph F. Savelli - West Chester OH
James N. Cooper - Hamilton OH
Byron A. Pritchard - Loveland OH

General Electric Company - Cincinnati OH

F23R 360, F02C 722

60748

A carburetor for the combustor of a gas turbine engine wherein a swirler and a venturi cooperate to atomize and mix air and fuel for the combustor, wherein a downstream mounted integrally formed sleeve and splash plate is provided to control the flow of the air/fuel mixture into the combustor. The integral splash plate and sleeve has protuberances formed on its upstream surface to increase the area impinged by cooling air and thereby enhance cooling of the splash plate flange thereof.

5375420, Dec 27, 1994

Aug 12, 1993

8/105772

Stephen W. Falls - Cincinnati OH
Hubert S. Roberts - Cincinnati OH
James N. Cooper - Hamilton OH
Stephen E. Melton - West Chester OH

General Electric Company - Cincinnati OH

F02C 700

60747

A double annular combustor having concentrically disposed inner and outer annular combustors is provided with inner and outer domes. A centerbody is disposed between the inner and outer domes and is constructed of a plurality of annular segments. Each segment includes an upper wall, a lower wall, an upstream wall and a downstream end. The upper and lower walls include flanges extending therefrom to form cavities, within which are cooling holes. Pins are also provided which extend between the upper and lower walls of the centerbody to augment the cooling and structural connection thereof.

7665308, Feb 23, 2010

Nov 7, 2005

11/268183

Mark Durbin - Springboro OH, US
Allen M. Danis - Mason OH, US
Timothy J. Held - Blanchester OH, US
James N. Cooper - Hamilton OH, US
Douglas Marti Fortuna - Cincinnati OH, US
Daniel Durstock - Forth Wright KY, US

General Electric Company - Schenectady NY

F02C 3/30

60775, 60 3955, 239549

A method facilitates operating a gas turbine engine. The method comprises supplying steam to a nozzle, supplying primary fuel to the nozzle, discharging the steam into a combustor from a plurality of circumferentially-spaced steam outlets defined in a tip of the nozzle, and discharging the primary fuel into the combustor from at least one outlet that is spaced circumferentially between the steam outlets.

7010923, Mar 14, 2006

Aug 30, 2004

10/929805

Alfred A. Mancini - Cincinnati OH, US
Michael L. Vermeersch - Hamilton OH, US
Duane D. Thomsen - Loveland OH, US
Allen M. Danis - Mason OH, US
James N. Cooper - Hamilton OH, US
Steven J. Lohmueller - Reading OH, US
Hukam C. Mongia - Westchester OH, US

General Electric Company - Schenectady NY

F02C 7/00

60776

A method for operating a gas turbine engine facilitates reducing an amount of emissions from a combustor. The combustor includes a mixer assembly including a pilot mixer, a main mixer, and a centerbody that extends therebetween. The pilot mixer includes a pilot fuel nozzle and a plurality of axial swirlers. The main mixer includes a main swirler and a plurality of fuel injection ports. The method comprises injecting fuel into the combustor through the pilot mixer, such that the fuel is discharged downstream from the pilot mixer axial swirlers, and directing flow exiting the pilot mixer with a lip extending from the centerbody into a pilot flame zone downstream from said pilot mixer.

2005021, Oct 6, 2005

Mar 31, 2004

10/814488

William Myers - West Chester OH, US
Thomas Ng - West Chester OH, US
Alfred Mancini - Cincinnati OH, US
James Cooper - Hamilton OH, US

F02C007/22

060739000, 060740000

A multi-staged gas turbine engine fuel supply fuel injector includes at least first and second staged fuel injection circuits having first and second fuel injection points. At least first and second fuel nozzle valves operable to open at different first and second crack open pressures are controllably connected to the first and second staged fuel injection circuits, respectively. A single fuel supply manifold is connected to all of the fuel nozzle valves. A single fuel signal manifold is controllably connected to all of the first and second fuel nozzle valves. The fuel injector includes a valve housing containing the fuel nozzle valves.

7036302, May 2, 2006

Mar 15, 2004

10/801439

William Joseph Myers Jr. - West Chester OH, US
Thomas Vander Ng - West Chester OH, US
Alfred Albert Mancini - Cincinnati OH, US
James Neil Cooper - Hamilton OH, US

General Electric Company - Schenectady NY

F02C 7/232

60 39281, 60741, 60742

A multi-staged gas turbine engine fuel supply system includes a plurality of fuel injectors and at least first and second staged fuel injection circuits in each of the fuel injectors. Each of the first and second staged fuel injection circuits includes first and second fuel injection points and at least first and second fuel nozzle valves operable to open at different first and second crack open pressures and controllably connected to the first and second staged fuel injection circuits, respectively. A single fuel supply manifold is connected to all of the fuel nozzle valves. A single fuel signal manifold is controllably connected to all of the first and second fuel nozzle valves. The fuel injector may have a valve housing with one of the first fuel nozzle valves and one of the second fuel nozzle valves contained therein.