Matthew W Wilson

US Patent:

20100024425, Feb 4, 2010

Filed:

Jul 31, 2008

Appl. No.:

12/183098

Inventors:

David W. Cihlar - Greenville SC, US
William L. Byrne - Simpsonville SC, US
Marcus B. Huffman - Simpsonville SC, US
Matthew B. Wilson - Greer SC, US

International Classification:

F02C 7/22
B05B 1/00
F23R 3/28

US Classification:

60734, 239589

Abstract:

A fuel nozzle for a gas turbine combustor that includes an extended flange. At a first end, the extended flange may be configured to engage an end cover, thereby securing the position of the fuel nozzle within the combustor. At a second end, the extended flange may be configured to engage a swozzle, within which a supply of fuel and compressed air is mixed during the operation of the combustor. The extended flange may be formed as a single piece.

US Patent:

20140033717, Feb 6, 2014

Filed:

Aug 3, 2012

Appl. No.:

13/566286

Inventors:

Ansley Michelle PANGLE - Pickens SC, US
Matthew Bernard WILSON - Greer SC, US
William Michael POSCHEL - Greenville SC, US

Assignee:

GENERAL ELECTRIC COMPANY - Schenectady NY

International Classification:

F23R 3/42

US Classification:

60722

Abstract:

A support structure for a burner tube in a combustor cap assembly for a gas turbine combustor includes an outer annular ring; an inner annular hub; and a plurality of struts extending radially between said outer annular ring and the inner hub. The inner hub is provided with a piston ring groove and a piston ring adapted to receive and seal an inner end of the burner tube.

US Patent:

20190178496, Jun 13, 2019

Filed:

Dec 11, 2017

Appl. No.:

15/838193

Inventors:

- Schenectady NY, US
James Harper - Greenville SC, US
Matthew Bernard Wilson - Greer SC, US
Robert Wade Clifford - Chesnee SC, US
Yon Han Chong - Greer SC, US
Gilbert Otto Kraemer - Greer SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F23R 3/06
F23R 3/00

Abstract:

A thimble assembly, which directs fluid flow through a combustor liner, includes a thimble boss and a thimble. The thimble boss is mounted an outer surface of the liner and surrounds a liner opening, thus defining a thimble boss passage. The thimble is disposed through the passage and the liner opening. The thimble wall extends from an inlet portion to an outlet of the thimble. The inlet portion has a greater diameter than the outlet and defines an inlet plane and a parallel intermediate plane. A terminal plane, parallel to the intermediate plane, includes an array of points most distant from a corresponding array of points defining the intermediate plane. The thimble wall has a non-uniform length, such that the outlet of the thimble is oriented at an oblique angle relative to the terminal plane. The thimble wall may have an arcuate shape defined as one-fourth of an ellipse.

US Patent:

20190178497, Jun 13, 2019

Filed:

Dec 11, 2017

Appl. No.:

15/838172

Inventors:

- Schenectady NY, US
James Harper - Greenville SC, US
Matthew Bernard Wilson - Greer SC, US
Robert Wade Clifford - Chesnee SC, US
Yon Han Chong - Greer SC, US
Benjamin Robert Ryan - Simpsonville SC, US
Gilbert Otto Kraemer - Greer SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F23R 3/28
F23R 3/00

Abstract:

An injection assembly for a gas turbine combustor having a liner defining a combustion zone and a secondary combustion zone and a forward casing circumferentially surrounding at least a portion of the liner is provided. The injection assembly includes a thimble assembly and an injector unit. The thimble assembly, which is mounted to the liner, includes a thimble that extends through a thimble aperture in the liner. The injector unit, which is mounted to and extends through the forward casing, includes an injector blade that extends into the thimble. The injection assembly introduces a flow of fuel into a flow of air flowing through the thimble, such that fuel and air are injected into the secondary combustion zone in a direction transverse to a flow of combustion products from the primary combustion zone.