Jason Charles Terry

US Patent:

20100170216, Jul 8, 2010

Filed:

Jan 7, 2009

Appl. No.:

12/349831

Inventors:

Krishna Kumar Venkataraman - Simpsonville SC, US
Roy Marshall Washam - Clinton SC, US
Hasan Karim - Simpsonvile SC, US
Jason Charles Terry - Greenville SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F02C 7/22

US Classification:

60 3937, 60737

Abstract:

A gas turbine engine is provided and includes a late lean injection (LLI) compatible combustor having a first interior in which a first fuel supplied thereto by a fuel circuit is combustible, a turbine, a transition zone, including a second interior in which a second fuel supplied thereto by the fuel circuit and the products of the combustion of the first fuel are combustible, the transition zone being disposed to fluidly couple the combustor and the turbine to one another, and a plurality of fuel injectors, which are structurally supported by the transition zone and coupled to the fuel circuit, and which are configured to supply the second fuel to the second interior in any one of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages.

US Patent:

20100170251, Jul 8, 2010

Filed:

Jan 7, 2009

Appl. No.:

12/349791

Inventors:

Krishna Kumar Venkataraman - Simpsonville SC, US
Willy Steve Ziminsky - Simpsonville SC, US
Jason Charles Terry - Greenville SC, US

Assignee:

GENERAL ELECTRIC COMPANY - Schenectady NY

International Classification:

F02C 7/22
F02C 7/00
F02C 3/04

US Classification:

60740, 60750, 60805

Abstract:

A gas turbine engine is provided and includes a fuel circuit, including multiple fuel circuit branches, a combustor having a first interior in which a first fuel supplied thereto by any one of the multiple fuel circuit branches is combustible, a turbine, a transition zone, including a second interior in which a second fuel supplied thereto by any one of the multiple fuel circuit branches, the second fuel including gas receivable by the fuel circuit from an external source, and the products of the combustion of the first fuel are combustible, the transition zone being disposed to fluidly couple the combustor and the turbine to one another, and a plurality of fuel injectors which supply the second fuel to the second interior in any one of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages.

US Patent:

20100170252, Jul 8, 2010

Filed:

Jan 7, 2009

Appl. No.:

12/349896

Inventors:

Krishna Kumar Venkataraman - Simpsonville SC, US
Jason Charles Terry - Greenville SC, US

Assignee:

General Electric Company - Schenectady NJ

International Classification:

F02C 1/00

US Classification:

60742, 701100

Abstract:

A gas turbine engine is provided and includes a combustor having a first interior in which a first fuel is combustible, the first fuel including natural gas and/or a blend of natural gas and alternate gas receivable by a fuel circuit from an external source, a turbine, a transition zone, including a second interior in which a second fuel, the second fuel including an unblended supply of the alternate gas receivable by the fuel circuit from the external source, and the products of the combustion of the first fuel are combustible, and a plurality of fuel injectors, which are structurally supported by the transition zone and coupled to the fuel circuit, and which are configured to supply the second fuel to the second interior in any one of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages.

US Patent:

20100170254, Jul 8, 2010

Filed:

Jan 7, 2009

Appl. No.:

12/349744

Inventors:

Krishna Kumar Venkataraman - Simpsonville SC, US
Jason Charles Terry - Greenville SC, US
Chetan Babu Velkur - Bangalore, IN
Hasan Karim - Simpsonville SC, US

Assignee:

GENERAL ELECTRIC COMPANY - Schenectady NY

International Classification:

F02C 7/22

US Classification:

60746

Abstract:

A gas turbine engine is provided and includes a combustor having a first interior in which a first fuel supplied thereto is combustible, a turbine, including rotating turbine blades, into which products of at least the combustion of the first fuel are receivable to power a rotation of the turbine blades, a transition zone, including a second interior in which a second fuel supplied thereto and the products of the combustion of the first fuel are combustible, the transition zone being disposed to fluidly couple the combustor and the turbine to one another, and a plurality of fuel injectors, which are supported by the transition zone and coupled to a fuel circuit, and which are configured to supply the second fuel to the second interior in any one or more of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages.

US Patent:

20140366541, Dec 18, 2014

Filed:

Jun 14, 2013

Appl. No.:

13/917964

Inventors:

- Schenectady NY, US
Bryan Wesley Romig - Simpsonville SC, US
Jason Thurman Stewart - Greer SC, US
Jason Charles Terry - Greenville SC, US

International Classification:

F02C 7/22

US Classification:

60734

Abstract:

A gas turbine engine having a combustor that includes: an inner radial wall defining a first interior chamber and a second interior chamber, wherein the first interior chamber extends axially from an end cover to a primary fuel injector, and the second interior chamber extends axially from the primary fuel injector to the turbine; an outer radial wall formed about the inner radial wall so that a flow annulus is formed therebetween; upstream fuel nozzles jutting into the flow annulus from the outer radial wall. The upstream fuel nozzles may include non-uniform circumferential spacing about the inner radial wall.

US Patent:

20140311150, Oct 23, 2014

Filed:

Apr 17, 2013

Appl. No.:

13/864708

Inventors:

- Schenectady NY, US
Gregory Earl Jensen - Greenville SC, US
Jason Charles Terry - Greenville SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F23R 3/28
F23R 3/14

US Classification:

60737, 60748

Abstract:

A fuel nozzle for use in a gas turbine includes a pre-mix flow passage for directing a flow segment of a flow of a working fluid through the fuel nozzle. A first swirler vane and a second swirler vane extend within the pre-mix flow passage. The first swirler vane provides a first wake region within the flow segment. The second swirler vane provides a second wake region within the flow segment. A fuel injection peg is disposed downstream from the first swirler vane and the second swirler vane. The fuel injection peg is positioned within the flow segment between the first wake region and the second wake region.