Amy K Hanson

US Patent:

20090188256, Jul 30, 2009

Filed:

Jan 25, 2008

Appl. No.:

12/020133

Inventors:

Gregory O. Woodcock - Mesa AZ, US
Amy T. Hanson - Peoria AZ, US
Robert S. Reynolds - Tempe AZ, US
Mike Armstrong - Phoenix AZ, US

Assignee:

Honeywell International Inc. - Morristown NJ

International Classification:

F02G 3/00

US Classification:

60754

Abstract:

A combustor for a turbine engine includes an outer liner and an inner liner circumscribed by the outer liner to form a combustion chamber therewith in which an air and fuel mixture is combusted to form streamlines of combustion gases. A first plurality of effusion cooling holes is formed in at least one of the inner or outer liners, with the first plurality of effusion cooling holes being oriented as a function of the streamlines.

US Patent:

20090293486, Dec 3, 2009

Filed:

Oct 26, 2007

Appl. No.:

11/925347

Inventors:

Amy T. Hanson - Peoria AZ, US
Ronald B. Pardington - Gilbert AZ, US

Assignee:

HONEYWELL INTERNATIONAL, INC. - Morristown NJ

International Classification:

F02C 1/00
F02C 7/264

US Classification:

60752, 60 39821

Abstract:

A combustor for a gas turbine engine is provided, and includes an inner case; an outer case circumscribing the inner case and forming an annular pressure vessel therebetween; an inner liner positioned within the annular pressure vessel; an outer liner circumscribing the inner liner and forming a combustion chamber with the inner liner; and an igniter coupled to the outer case and extending to the outer liner such that the igniter is positioned to ignite an air and fuel mixture in the combustion chamber. The igniter includes a protrusion for coupling the igniter to the outer liner.

US Patent:

20110120132, May 26, 2011

Filed:

Nov 23, 2009

Appl. No.:

12/623622

Inventors:

Nagaraja S. Rudrapatna - Chandler AZ, US
Paul Yankowich - Phoenix AZ, US
Amy Hanson - Peoria AZ, US

Assignee:

HONEYWELL INTERNATIONAL INC. - Morristown NJ

International Classification:

F23R 3/42
F02C 7/264

US Classification:

60752, 60 39821

Abstract:

A combustor for a gas turbine engine includes an inner liner and an outer liner circumscribing the inner liner and forming a combustion chamber therewith. The outer liner is a dual walled liner with a first wall and a second wall. A fuel igniter includes a tip portion configured to ignite an air and fuel mixture in the combustion chamber. An igniter support assembly positions the fuel igniter relative to the combustion chamber. The igniter support assembly defines a plurality of holes configured to direct cooling air toward the tip portion of the fuel igniter. The igniter support assembly includes first and second floating seals that are configured to accommodate radial and axial relative movements.

US Patent:

20110120133, May 26, 2011

Filed:

Nov 23, 2009

Appl. No.:

12/623773

Inventors:

Nagaraja S. Rudrapatna - Chandler AZ, US
Paul Yankowich - Phoenix AZ, US
Amy Hanson - Peoria AZ, US

Assignee:

HONEYWELL INTERNATIONAL INC. - Morristown NJ

International Classification:

F23D 14/46

US Classification:

60752

Abstract:

A combustor for a turbine engine is provided. The combustor includes a first liner and a second liner forming a combustion chamber. The combustion chamber is configured to receive an air-fuel mixture for combustion therein and having a longitudinal axis that defines axial and radial directions. The first liner is a first dual walled liner having a first hot wall facing the combustion chamber and a first cold wall that forms a first liner cavity with the first hot wall, the first liner cavity having first and second ends. A first liner seal is configured to seal the second end of the first liner cavity and to accommodate relative movement of the first hot wall and first cold wall generally in the axial and radial directions.