Beverly R Duncan

6389815, May 21, 2002

Sep 8, 2000

09/658872

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

General Electric Company - Schenectady NY

F02C 722

60746, 60748

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.

6851263, Feb 8, 2005

Oct 29, 2002

10/282520

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

General Electric Company - Schenectady NY

F02C001/00

60750, 60752, 60755

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.

8555645, Oct 15, 2013

Jul 21, 2008

12/176898

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

General Electric Company - Schenectady NY

F02C 7/22

60737, 60740

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.

61453196, Nov 14, 2000

Jul 16, 1998

9/116509

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

General Electric Company - Cincinnati OH

F02C 100

60755

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.

62057898, Mar 27, 2001

Nov 13, 1998

9/191558

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

General Electric Company - Cincinnati OH

F23R3/06

60754

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.