Beverly S Duncan

US Patent:

6389815, May 21, 2002

Filed:

Sep 8, 2000

Appl. No.:

09/658872

Inventors:

Harjit Singh Hura - Cincinnati OH
Paul Edward Sabla - Cincinnati OH
James Neil Cooper - Hamilton OH
Beverly Stephenson Duncan - West Chester OH
Hukam Chand Mongia - West Chester OH
Steven Joseph Lohmueller - Reading OH

Assignee:

General Electric Company - Schenectady NY

International Classification:

F02C 722

US Classification:

60746, 60748

Abstract:

A two-stage fuel nozzle assembly for a gas turbine engine. The primary combustion region is centrally positioned and includes a fuel injector that is surrounded by one or more swirl chambers to provide a fuel air mixture that is ignited to define a first stage combustion zone. A secondary combustion region is provided by an annular housing that surrounds the primary combustion region, and it includes a secondary fuel injector having a radially outwardly directed opening and surrounded by an annular ring that includes openings for providing a swirl chamber for the secondary combustion region. Cooling air is directed angularly between the primary and secondary combustion zones to delay intermixing and thereby allow more complete combustion of the respective zones prior to their coalescing further downstream. The primary combustion region is activated during idle and low engine power conditions and both the primary and secondary combustion regions are activated during high engine power conditions.

US Patent:

6851263, Feb 8, 2005

Filed:

Oct 29, 2002

Appl. No.:

10/282520

Inventors:

James Anthony Stumpf - Milford OH, US
Beverly Stephenson Duncan - West Chester OH, US
David Louis Burrus - Cincinnati OH, US
Clayton Stuart Cooper - Loveland OH, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F02C001/00

US Classification:

60750, 60752, 60755

Abstract:

A liner for a gas turbine engine combustor having a trapped vortex cavity formed therein, wherein a dome plate is positioned at an upstream end of the combustor, includes: a first portion positioned adjacent and connected to the dome plate, wherein the first liner portion extends downstream from and substantially perpendicular to the dome plate; a second portion extending substantially perpendicular to the first liner portion and substantially parallel to the dome plate; a first arcuate portion having a predetermined radius located between the first and second liner portions; a third portion extending downstream and substantially perpendicular to the second liner portion; and, a second arcuate portion located between the second and third liner portions; wherein the first liner portion, the second liner portion, the first arcuate liner portion and a portion of the dome plate form the trapped vortex cavity.

US Patent:

8555645, Oct 15, 2013

Filed:

Jul 21, 2008

Appl. No.:

12/176898

Inventors:

Beverly Stephenson Duncan - West Chester OH, US
Michael Anthony Benjamin - Cincinnati OH, US
George Chia-Chun Hsiao - West Chester OH, US
Hukam Chand Mongia - West Chester OH, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F02C 7/22

US Classification:

60737, 60740

Abstract:

A fuel nozzle centerbody is provided that includes a cylindrical cross-sectional area, and a baffle co-axially aligned within the centerbody. The baffle includes a plurality of circumferentially-spaced apertures configured to channel an airflow radially outward such that the channeled airflow impinges a centerbody inner surface.

US Patent:

61453196, Nov 14, 2000

Filed:

Jul 16, 1998

Appl. No.:

9/116509

Inventors:

Craig P. Burns - Mason OH
Beverly S. Duncan - West Chester OH
James E. Thompson - Middletown OH
Glenn E. Wiehe - Mt. Healthy OH

Assignee:

General Electric Company - Cincinnati OH

International Classification:

F02C 100

US Classification:

60755

Abstract:

A combustor liner includes a wall having an outboard surface and an opposite inboard surface. A plurality of first holes are inclined through the wall in a multihole pattern to channel cooling fluid therethrough to form a cooling film layer along the inboard surface. A second hole extends perpendicularly through the wall within the multihole pattern to form a shadow along the inboard surface devoid of the first holes. A transition hole extends through the wall in the shadow at a greater inclination than the first holes for cooling the wall at the shadow.

US Patent:

62057898, Mar 27, 2001

Filed:

Nov 13, 1998

Appl. No.:

9/191558

Inventors:

David B. Patterson - Mason OH
Beverly S. Duncan - West Chester OH
Mark G. Rettig - Cinncinnati OH
James E. Thompson - Middletown OH
Glenn E. Wiehe - Mt. Healthy OH

Assignee:

General Electric Company - Cincinnati OH

International Classification:

F23R3/06

US Classification:

60754

Abstract:

Multi-hole film cooling of combustor liners is enhanced by providing clustered groups of cooling holes in areas of the liners that would otherwise experience a loss of cooling film effectiveness. The combustor liner is made up of a shell having first and second groups of cooling holes formed therein. The cooling holes of the second group are more closely spaced than the cooling holes of the first group. The second group of cooling holes is located on an area of the shell where the cooling film effectiveness is degraded. Preferred locations include a region of the shell that is subjected to swirl impingement and a spot immediately downstream of a large opening in the shell such as a dilution hole, a borescope hole or an igniter port hole.

US Patent:

20190113235, Apr 18, 2019

Filed:

Oct 17, 2017

Appl. No.:

15/785726

Inventors:

- Schenectady NY, US
Joseph Zelina - Waynesville OH, US
Eric John Stevens - Mason OH, US
Clayton Stuart Cooper - Loveland OH, US
Beverly Stephenson Duncan - West Chester OH, US
Juntao Zhang - Mason OH, US

International Classification:

F23R 3/58
F23R 3/14

Abstract:

A trapped vortex combustor for use in a gas turbine engine defines a radial direction, an axial direction, and a circumferential direction. The trapped vortex combustor includes an outer vortex chamber wall defining a forward end, and a dome attached to, or formed integrally with, the outer vortex chamber wall at the forward end of the outer vortex chamber wall. The dome and outer vortex chamber wall define at least in part a combustion chamber having an outer trapped vortex chamber. The dome includes an air chute defining an airflow direction. The radial direction and axial direction of the trapped vortex combustor define a reference plane extending through the air chute, the airflow direction of the air chute defining an angle greater than zero with the reference plane.

US Patent:

20190063753, Feb 28, 2019

Filed:

Aug 23, 2017

Appl. No.:

15/684083

Inventors:

- Schenectady NY, US
Mark David Durbin - Springboro OH, US
Randall Charles Boehm - Loveland OH, US
Michael Anthony Benjamin - Cincinnati OH, US
Beverly Stephenson Duncan - West Chester OH, US
Jeffrey Lyal Powell - Maineville OH, US

International Classification:

F23R 3/34
F23R 3/14
F23R 3/28

Abstract:

Fuel nozzle assemblies are provided. For example, a fuel nozzle assembly for a combustor system comprises a fuel nozzle having a pilot swirler and an outlet defined in an outlet end, as well as a main mixer attached to the outlet end and extending about the outlet. A total combustor airflow through the combustor system comprises a pilot swirler airflow that is greater than about 14% and a main mixer airflow that is less than about 50% of the total combustor airflow. In further embodiments, the fuel nozzle also comprises main and pilot fuel injectors that each are configured to receive a portion of a fuel flow to the fuel nozzle. The fuel nozzle provides less than about 80% of the fuel flow to the main fuel injector at a high power operating condition of a gas turbine engine in which the fuel nozzle assembly is installed.