Scott J Simmons

US Patent:

7861528, Jan 4, 2011

Filed:

Aug 21, 2007

Appl. No.:

11/892298

Inventors:

Geoffrey D. Myers - Simpsonville SC, US
Scott Simmons - Greenville SC, US
Stephen R. Thomas - Simpsonville SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F02C 1/00

US Classification:

60737, 60740

Abstract:

A fuel nozzle having a dedicated circuit to cool the diffusion tip with lower part count and reduced complexity. More specifically, the proposed design uses an independent circuit to cool the tip with diffusion fuel or purge air. An impingement plate may be provided to augment the cooling effect.

US Patent:

8161750, Apr 24, 2012

Filed:

Jan 16, 2009

Appl. No.:

12/355263

Inventors:

Scott Robert Simmons - Simpsonville SC, US
Stephen Robert Thomas - Simpsonville SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F02C 1/00

US Classification:

60737, 60742, 60804, 60748, 60776

Abstract:

A turbomachine includes a compressor, a turbine, and a combustor operatively connected to the turbine. The turbomachine further includes a cap member mounted to the combustor. The cap member includes a first surface and a second surface. A combustion chamber is defined within the combustor. An injection nozzle is supported at the second surface of the cap member. The injection nozzle includes a first end that extends through an inner flow path to a second end. The first end is configured to receive an amount of a first fluid and the second end is configured to receive an amount of a second fluid. A mixture of the first and second fluids is discharged from the second end of the injection nozzle.

US Patent:

8220272, Jul 17, 2012

Filed:

Dec 4, 2008

Appl. No.:

12/328346

Inventors:

Joel Meador Hall - Mauldin SC, US
Sergey Adolfovich Oskin - Saint-Petersburg, RU
Scott Robert Simmons - Simpsonville SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F02C 1/00

US Classification:

60740, 60 39463

Abstract:

A combustor housing includes an inlet cover plate having a central inlet configured to receive a supply of one of a high BTU content fuel or air and at least one radially-spaced, peripheral fuel inlet configured to receive a supply of a low BTU content fuel. It also includes an outlet cover plate having at least one radially-spaced, peripheral fuel outlet. The combustor housing also includes a peripheral sidewall joining the inlet cover and the outlet cover and enclosing a plenum, the at least one peripheral fuel inlet opening through the inlet cover plate into the plenum and the at least one fuel outlet opening from the plenum through the outlet cover plate. The central inlet opens into at least one conduit which extends away from the central inlet and opens into at least one high BTU content fuel conduit or air supply conduit that is axially aligned with the at least one fuel outlet.

US Patent:

8261554, Sep 11, 2012

Filed:

Sep 17, 2008

Appl. No.:

12/212576

Inventors:

Donald Mark Bailey - Simpsonville SC, US
Scott R. Simmons - Simpsonville SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F02C 1/00

US Classification:

60740, 60741

Abstract:

A system, in one embodiment, includes a fuel nozzle tip retainer that includes a structural member having a geometry that blocks a tip insert from moving axially downstream of a fuel nozzle.

US Patent:

8347631, Jan 8, 2013

Filed:

Mar 3, 2009

Appl. No.:

12/397240

Inventors:

Donald Mark Bailey - Simpsonville SC, US
Scott R Simmons - Simpsonville SC, US
Gregory Allen Boardman - Greer SC, US
Xiomara Irizarry-Rosado - Greer SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F02C 1/00
F02G 3/00

US Classification:

60740, 60742, 60 3955, 239422

Abstract:

In an embodiment, a system includes an end cover and a liquid cartridge. The liquid cartridge is configured to mount in a fuel nozzle of a turbine engine, wherein the liquid cartridge comprises a one piece flange configured to couple to the end cover, wherein the flange comprises a water inlet, an air inlet, and a fuel inlet.

US Patent:

8365535, Feb 5, 2013

Filed:

Feb 9, 2009

Appl. No.:

12/368011

Inventors:

Stanley Kevin Widener - Greenville SC, US
Scott Robert Simmons - Simpsonville SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F02C 1/00

US Classification:

60742, 60740

Abstract:

A fuel nozzle manifold comprising a flange, a stem and a swirler is provided. The flange has a first fluid inlet fluidly connected to a radially extending first flow passage, the stem includes at least a first axially extending and only partially circumferentially extending flow channel, and the swirler has at least a first radially extending premix passage. The flange and the stem can comprise a homogeneous component, or two separate components fluidly connecting the first axially extending flow channel to the first flow passage, to form a fluid connection between the flange and the stem, the swirler comprises another component fitted together with the flange and stem component and fluidly connecting the first premix passage and the first flow channel.

US Patent:

8484978, Jul 16, 2013

Filed:

Nov 12, 2009

Appl. No.:

12/617085

Inventors:

Donald Mark Bailey - Simpsonville SC, US
Scott Robert Simmons - Simpsonville SC, US
Marcus Byron Huffman - Simpsonville SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F02C 1/00

US Classification:

60740, 60737

Abstract:

A method of assembling a fuel nozzle assembly for a gas turbine engine having a natural operating frequency includes providing a flange and providing a premix tube. The flange is fabricated from a first alloy such that the flange is configured to exhibit a first frequency that is different than the natural operating frequency of the gas turbine engine. The premix tube is fabricated from a second alloy such that the premix tube is configured to exhibit a second frequency that is different from the natural operating frequency of the gas turbine engine. The premix tube is coupled to the flange.

US Patent:

8505304, Aug 13, 2013

Filed:

Dec 1, 2008

Appl. No.:

12/325559

Inventors:

Geoffrey D. Myers - Simpsonville SC, US
Scott Simmons - Greenville SC, US
Stephen R. Thomas - Simpsonville SC, US
Donald Mark Bailey - Greenville SC, US
David Martin Johnson - Simpsonville SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F23R 3/14

US Classification:

60748, 60737, 60804

Abstract:

A fuel nozzle for use with a combustion chamber defined within a gas turbine engine and a method for assembling the same are provided. The fuel nozzle includes a swirler assembly and a burner tube that is coupled to a support flange in a detachable manner such that an inner surface of the burner tube circumscribes an outer surface of the swirler assembly during fuel nozzle operation.