Terrel E Kuhn

US Patent:

7124487, Oct 24, 2006

Filed:

Feb 5, 2004

Appl. No.:

10/774230

Inventors:

Terrel E. Kuhn - Mesa AZ, US
William G. Freeman - Fountain Hills AZ, US
Francis S. Maszk - Tempe AZ, US
Douglas P. Freiberg - Phoenix AZ, US
Kenneth A. Struzek - Gilbert AZ, US
Lawrence A. Kobold - Mesa AZ, US

Assignee:

Honeywell International, Inc. - Morristown NJ

International Classification:

B23P 17/04
B21D 53/00
F02C 1/00

US Classification:

294011, 2940201, 2940208, 2940211, 2989001

Abstract:

A method for controlling combustor liner carbon formation on repaired combustors includes making modular effusion panel subassemblies remote from the combustor liner; removing a non-effusion or damaged panel from the combustor liner; and replacing the non-effusion or damaged panel with the modular effusion panel.

US Patent:

7185497, Mar 6, 2007

Filed:

May 4, 2004

Appl. No.:

10/839116

Inventors:

Rodolphe Dudebout - Phoenix AZ, US
Terrel E. Kuhn - Mesa AZ, US
Paul R. Yankowich - Phoenix AZ, US
Frank J. Zupanc - Phoenix AZ, US

Assignee:

Honeywell International, Inc. - Morristown NJ

International Classification:

F23R 3/14
F23R 3/30
F23R 3/06

US Classification:

60776, 60737, 60748

Abstract:

A premix chamber for a combustor of a gas turbine engine comprises a cylindrical chamber having a premix chamber wall, the cylindrical chamber having a chamber inlet end longitudinally separated from a chamber outlet end along a central axis, a chamber inlet plate in communication with the premix chamber wall at the chamber inlet end, the chamber inlet plate having a fuel nozzle inlet hole disposed through the chamber inlet plate, the chamber inlet plate further comprising a plurality of swirler passages disposed through the chamber inlet plate, and the chamber outlet end being open. A method of producing turbine gas is also disclosed.

US Patent:

7812282, Oct 12, 2010

Filed:

Aug 7, 2007

Appl. No.:

11/835137

Inventors:

Terrel E. Kuhn - Mesa AZ, US
Sossity A. Flamand - Phoenix AZ, US
Gregory O. Woodcock - Mesa AZ, US
Rodolphe Dudebout - Phoenix AZ, US
Lowell Frye - Chandler AZ, US

Assignee:

Honeywell International Inc. - Morristown NJ

International Classification:

B23K 26/38

US Classification:

21912171

Abstract:

Methods are provided of forming a plurality of fan-shaped effusion holes on a combustor having a surface, each hole having an outlet on the combustor surface. The method may include rotating the combustor relative to a laser beam, and positioning the combustor to a first position where the laser beam is at a first predetermined angle relative to the combustor surface. The laser beam is pulsed at the combustor surface to form a first plurality of trepan cuts. The first predetermined angle is adjusted to a second position where the laser beam is at a second predetermined angle relative to the combustor surface. The laser beam is pulsed at each trepan cut of the first plurality of trepan cuts, to thereby form a cut for at least a portion of the fan shape of each effusion hole outlet, wherein each cut overlaps a trepan cut of the first plurality of trepan cuts.

US Patent:

8534076, Sep 17, 2013

Filed:

Jun 9, 2009

Appl. No.:

12/481441

Inventors:

Gregory O. Woodcock - Mesa AZ, US
Bradley Reed Tucker - Chandler AZ, US
Jason Smoke - Phoenix AZ, US
Stony Kujala - Tempe AZ, US
Terrel Kuhn - Mesa AZ, US

Assignee:

Honeywell Internationl Inc. - Morristown NJ

International Classification:

F02C 7/20
F04D 29/08
F01D 11/00

US Classification:

60800, 60796, 415138, 4151701, 4151742

Abstract:

A combustor-turbine seal interface is provided for deployment within a gas turbine engine. In one embodiment, the combustor-turbine assembly a combustor, a turbine nozzle downstream of the combustor, and a first compliant dual seal assembly. The first compliant dual seal assembly includes a compliant seal wall sealingly coupled between the combustor and the turbine nozzle, a first compression seal sealingly disposed between the compliant seal wall and the turbine nozzle, and a first bearing seal generally defined by the compliant seal wall and the turbine nozzle. The first bearing seal is sealingly disposed in series with the first compression seal.

US Patent:

20120304647, Dec 6, 2012

Filed:

Jun 6, 2011

Appl. No.:

13/154208

Inventors:

Rodolphe Dudebout - Phoenix AZ, US
Veeraraghava Raju Hasti - Bangalore, IN
Terrel Kuhn - Mesa AZ, US
Sunil James - Chandler AZ, US
Mario Scaini - Phoenix AZ, US

Assignee:

HONEYWELL INTERNATIONAL INC. - Morristown NJ

International Classification:

F23R 3/02
F23M 5/00
F23R 3/28

US Classification:

60732, 60755, 60740, 60754

Abstract:

A combustor for a gas turbine engine is provided. The combustor includes an inner liner; an outer liner circumscribing the inner liner; and a combustor dome having a first edge coupled to the inner liner and a second edge coupled to the outer liner. The combustor dome forms a combustion chamber with the inner liner and the outer liner. The combustion chamber receives air flow through the inner and outer liners, and the combustor dome is configured to bifurcate the air flow at the combustor dome into a first stream directed to the inner liner and a second stream directed to the outer liner.

US Patent:

6868675, Mar 22, 2005

Filed:

Jan 9, 2004

Appl. No.:

10/755560

Inventors:

Terrel E. Kuhn - Mesa AZ, US
William G. Freeman - Fountain Hills AZ, US
Francis S. Maszk - Tempe AZ, US
Douglas P. Freiberg - Phoenix AZ, US
Kenneth A. Struzek - Gilbert AZ, US
Lawrence A. Kobold - Mesa AZ, US

Assignee:

Honeywell International Inc. - Morristown NJ

International Classification:

F02C003/14

US Classification:

60772, 60752

Abstract:

An apparatus and method for controlling combustor liner carbon formation is provided. The apparatus includes a dome subassembly that is removeably affixed to a modular outer panel subassembly and a modular inner panel subassembly. Each panel subassembly includes panels that are removeably affixed to one another.

US Patent:

20140109581, Apr 24, 2014

Filed:

Oct 19, 2012

Appl. No.:

13/656219

Inventors:

- Morristown NJ, US
Terrel Kuhn - Mesa AZ, US
Vinayender Kuchana - Hyderabad, IN
Veeraraghava Raju Hasti - Bangalore, IN
Raymond Gage - Phoenix AZ, US
Sunil James - Chandler AZ, US

Assignee:

HONEYWELL INTERNATIONAL INC. - Morristown NJ

International Classification:

F23R 3/06
F23R 3/54
F23R 3/26

US Classification:

60732, 60752, 60754, 60760

Abstract:

A combustor for a gas turbine engine is provided. The combustor includes an annular inner liner; an annular outer liner circumscribing the annular inner liner; and a combustor dome having a first edge coupled to the annular inner liner and a second edge coupled to the annular outer liner, the combustor dome forming a combustion chamber with the annular inner liner and the annular outer liner. The combustion chamber accommodates fluid flow through the annular inner and annular outer liners. The combustion chamber converges in the direction of the air flow to reduce a diameter of the combustion chamber. The combustor dome is configured to bifurcate the air flow at the combustor dome into a first stream directed to the annular inner liner and a second stream directed to the annular outer liner.