James A Harper

US Patent:

8122725, Feb 28, 2012

Filed:

Nov 1, 2007

Appl. No.:

11/933898

Inventors:

Geoffrey David Myers - Simpsonville SC, US
David August Snider - Simpsonville SC, US
Eric Motter - Jacksonville FL, US
Daniel R. Tegel - Simpsonville SC, US
James Harper - Greenville SC, US
Stephen R. Watts - Greer SC, US
Joseph Citeno - Greenville SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F02C 7/22
F02C 9/26
F02C 9/00
F02C 3/00

US Classification:

60776, 60 3937, 60790, 60 39281

Abstract:

Methods and systems for delivering fuel in a gas turbine engine are provided. The system includes a plurality of can annular combustors that includes at least a first set of combustors of the plurality of can annular combustors and at least a second set of combustors of the plurality of can annular combustors wherein each set of combustors is supplied by a separately controllable respective fuel delivery system. The method includes supplying fuel at a first fuel schedule to the first set of combustors and supplying fuel at a second fuel schedule to the second set of combustors during a first mode of operation wherein the second fuel schedule is different than the first fuel schedule, and supplying fuel at the second fuel schedule to the first and second sets of combustors during a second mode of operation.

US Patent:

8479519, Jul 9, 2013

Filed:

Jan 7, 2009

Appl. No.:

12/350083

Inventors:

Wei Chen - Greer SC, US
William Lawrence Byrne - Simpsonville SC, US
Xiaoguang Yu - Greer SC, US
James Harper - Greenville SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F02C 1/00
F02G 3/00

US Classification:

60740, 60742, 60743

Abstract:

A method and apparatus for a diffusion tip for use with a fuel nozzle is described. The diffusion tip has a substantially circular body including an outer surface and an opposite inner surface. The diffusion tip body extends from a discharge end to an inlet end. The diffusion tip includes an inlet surface adjacent to the discharge end and defined within the body. A discharge surface is defined opposite the inlet surface. A plurality of diffusion apertures each extend between the discharge surface and the inlet surface, each aperture is oriented relative to the body to discharge a diffusion flow outward therefrom at an angle γ (gamma) measured in an X-Z plane between a centerline of the aperture and an X-axis extending tangentially to the outer surface, and at an angle θ (theta) measured in a Y-Z plane between the centerline of the aperture and a Y-axis extending radially outward from the centerline.

US Patent:

20070059844, Mar 15, 2007

Filed:

Sep 12, 2005

Appl. No.:

11/162485

Inventors:

James HARPER - Spartanburg SC, US
David TURNER - Roanoke VA, US
Kenneth JACOBSON - Alpharetta GA, US
Brian WEST - Clinton TN, US

Assignee:

TECHMER PM, LLC - Rancho Dominguez CA

International Classification:

C40B 40/04
C40B 30/02
G06Q 99/00

US Classification:

436518000, 524090000, 705001000

Abstract:

A pigment library and a method for preparing it are provided, which includes identifying a plurality of thermoplastic polymers and then selecting pigments useful in the plurality of thermoplastic polymers. The pigments are heat stable at the melt temperature of each of the plurality of thermoplastic polymers and are not chemically interactive or reactive with each of the polymers of the plurality of thermoplastic polymer. Further, each of the pigments in combination with each of the polymers of the plurality of thermoplastic polymers possesses the property of being lightfast, injection moldable, and fiber spinnable and also not crocking. A colorant database is then prepared using the pigment library. The colorant database is used with color matching software that predict formulations using the colorant database. The result is the development of formulations that minimize or eliminate metameric color effect under various lighting conditions across multiple polymers and end product types.

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.

US Patent:

20190178498, Jun 13, 2019

Filed:

Dec 11, 2017

Appl. No.:

15/838149

Inventors:

- Schenectady NY, US
James Harper - Greenville SC, US
Yon Han Chong - Greer SC, US
Charlie Edmond Jones - Greenville SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F23R 3/34
F23R 3/28

Abstract:

A gas turbine combustor includes: a head end comprising a primary fuel nozzle; a liner defining a primary combustion zone proximate the head end and a downstream secondary combustion zone; a forward casing radially outward of and surrounding at least a portion of the liner; and an axial fuel staging system. The axial fuel staging system includes a plurality of fuel injection assemblies. Each fuel injection assembly includes a thimble assembly mounted to the liner, and an injector unit attached to the forward casing. A thimble of the thimble assembly extends through a thimble aperture in the liner. The injector unit extends through the forward casing, such that a portion of the injector unit is disposed within the thimble, and a fuel line fitting is disposed outward of the forward casing. The injector unit introduces fuel into air flowing through the thimble for injection into the secondary combustion zone.

US Patent:

20180149363, May 31, 2018

Filed:

Dec 27, 2016

Appl. No.:

15/391450

Inventors:

- Schenectady NY, US
Mihir Lal - Greenville SC, US
James Harper - Greenville SC, US
Douglas Edward Dean - Greenville SC, US
Abhijit Prabhakar Kulkarni - HITEC City, IN

International Classification:

F23R 3/34
F02C 9/26
F02C 9/28

Abstract:

This disclosure relates to systems and methods for tuning combustion dynamics in a combustor. In one embodiment of the disclosure, a method includes providing, via at least one sensor, combustion dynamics amplitude data associated with a combustor. Method may allow monitoring, by an equipment controller communicatively coupled to the at least one sensor, the combustion dynamics amplitude data. The method may allow detecting at least one change in acoustic pressure amplitude associated with combustion in the combustor. In response to detecting the change in the acoustic pressure amplitude, the method proceeds with determining a fuel split change to at least two fuel circuits configured to supply fuel to the combustor, and applying the fuel split change to the combustor.

US Patent:

20170363293, Dec 21, 2017

Filed:

Jun 21, 2016

Appl. No.:

15/188163

Inventors:

- Schenectady NY, US
James Harper - Greenville SC, US
Yon Han Chong - Greer SC, US

International Classification:

F23R 3/28
F02C 7/22

Abstract:

A premix pilot nozzle is disclosed herein. The premix pilot nozzle includes a nozzle body. The nozzle body includes a forward wall, an aft wall, an outer band that extends between the forward wall and the aft wall and a tip portion that extends axially downstream from the aft wall. The nozzle body further defines a fuel inlet plenum that extends coaxially within the nozzle body, a fuel distribution plenum that is defined within the nozzle body radially outwardly from and in fluid communication with the fuel inlet plenum, a plurality of premix passages that extend helically around the fuel inlet plenum within the fuel distribution plenum and a plurality of air passages annularly arranged around the plurality of premix passages. One or more premix passages of the plurality of premix passages are in fluid communication with the fuel distribution plenum.