Thomas J Bronson

US Patent:

8141365, Mar 27, 2012

Filed:

Feb 27, 2009

Appl. No.:

12/394656

Inventors:

Thomas J. Bronson - Mesa AZ, US
Frank Joseph Zupanc - Phoenix AZ, US

Assignee:

Honeywell International Inc. - Morristown NJ

International Classification:

F23R 3/06
F23R 3/50

US Classification:

60754, 60752, 60755, 60804

Abstract:

A combustor may include an outer liner having a first row and a second row of circumferentially distributed air admission holes. The second row of the outer liner may be downstream of the first row of the outer liner, and the air admission holes of the first row of the outer liner may be larger than the air admission holes of the second row of the outer liner. An inner liner is circumscribed by the outer liner and has a third and fourth row of circumferentially distributed air admission holes. The air admission holes of the third row of the inner liner may be larger than the air admission holes of the fourth row of the inner liner. The inner and outer liners may form a combustion chamber, and at least a portion of the air admission holes of the first, second, third, or fourth rows may be plunged.

US Patent:

8171740, May 8, 2012

Filed:

Feb 27, 2009

Appl. No.:

12/394725

Inventors:

Thomas J. Bronson - Mesa AZ, US
Frank Joseph Zupanc - Phoenix AZ, US

Assignee:

Honeywell International Inc. - Morristown NJ

International Classification:

F23R 3/06
F23R 3/50

US Classification:

60804, 60754, 60732

Abstract:

A combustor may include an outer liner having a first group of air admission holes and defining a plurality of outer liner regions. The combustor may further include an inner liner having a second group of air admission holes and defining a plurality of inner liner regions. The first group of air admission holes within a respective outer liner region may include a first plunged air admission hole approximately axially aligned with the respective fuel injector, a second plunged air admission hole approximately on the outer boundary line between the respective outer liner region and a first adjacent outer liner region, the first air admission hole being downstream of the second air admission hole, and a third plunged air admission hole approximately on the outer boundary line between the respective outer liner region and a second adjacent outer liner region.

US Patent:

8584466, Nov 19, 2013

Filed:

Mar 9, 2010

Appl. No.:

12/720431

Inventors:

Thomas J. Bronson - Mesa AZ, US
Frank J. Zupanc - Phoenix AZ, US

Assignee:

Honeywell International Inc. - Morristown NJ

International Classification:

F02C 1/00
F02G 3/00

US Classification:

60752

Abstract:

A combustor for a turbine engine is provided. The combustor includes a first liner; a second liner positioned relative to the first liner to form a combustion chamber therebetween, the combustion chamber configured to receive a fuel-air mixture; an igniter positioned relative to the combustion chamber and configured to ignite the fuel-air mixture; a first group of air admission holes positioned in the first liner and forming a regular circumferential pattern around the first liner; and a second group of air admission holes positioned in the first liner at a first circumferential position corresponding to the igniter, the second group of air admission holes departing from the regular circumferential pattern.

US Patent:

8616004, Dec 31, 2013

Filed:

Oct 28, 2009

Appl. No.:

12/607815

Inventors:

Frank J. Zupanc - Phoenix AZ, US
Thomas J. Bronson - Mesa AZ, US

Assignee:

Honeywell International Inc. - Morristown NJ

International Classification:

F02C 3/14

US Classification:

60754

Abstract:

A combustor for a turbine engine includes an outer liner having a first group of air admission holes and defining a plurality of outer liner regions. The combustor further includes an inner liner circumscribed by the outer liner and forming a combustion chamber therebetween, the inner liner having a second group of air admission holes and defining a plurality of inner liner regions. The combustor further includes a plurality of fuel injectors extending into the combustion chamber and configured to deliver an air-fuel mixture to the combustion chamber, each of the plurality of fuel injectors being associated with one of the outer liner regions and one of the inner liner regions. The first group within a respective outer liner region includes air admission holes that circumferentially alternate between approximately a first size and approximately a second size, the first size being different than the second size.

US Patent:

20080314044, Dec 25, 2008

Filed:

Jun 22, 2007

Appl. No.:

11/767306

Inventors:

Thomas J. Bronson - Mesa AZ, US
Rodolphe Dudebout - Phoenix AZ, US

Assignee:

HONEYWELL INTERNATIONAL, INC. - Morristown NJ

International Classification:

F02C 7/12

US Classification:

60754, 60752

Abstract:

A combustor includes an inner liner; an outer liner circumscribing the inner liner and forming a combustion chamber with the inner liner; a combustor dome coupled to the inner and outer liners; and a plurality of heat shields coupled to combustor dome. Each of the heat shields includes a heat shield plate defined by a first edge facing the inner liner and a second edge facing the outer liner; and a plurality of baffles extending from the heat shield plate. Each of the plurality of baffles includes two ribs and a connection portion connecting the two ribs to form a closed portion and an opposite open portion. The open portion of each of the plurality of baffles faces the first edge or the second edge.

US Patent:

20100212324, Aug 26, 2010

Filed:

Feb 26, 2009

Appl. No.:

12/393729

Inventors:

Thomas J. Bronson - Mesa AZ, US
Nagaraja Rudrapatna - Chandler AZ, US
Jon Kettinger - Litchfield Park AZ, US
Frank Joseph Zupanc - Phoenix AZ, US

Assignee:

HONEYWELL INTERNATIONAL INC. - Morristown NJ

International Classification:

F02C 7/22
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 with the inner liner. The outer liner is a dual walled liner with a first wall and a second wall. The combustor includes a fuel igniter comprising a tip portion configured to ignite an air and fuel mixture in the combustion chamber and an igniter tube positioning the fuel igniter relative to the combustion chamber. The igniter tube includes a plurality of holes configured to direct cooling air toward the tip portion of the fuel igniter.

US Patent:

20110023495, Feb 3, 2011

Filed:

Jul 30, 2009

Appl. No.:

12/512816

Inventors:

Thomas J. Bronson - Mesa AZ, US
Frank Joseph Zupanc - Phoenix AZ, US
Paul Yankowich - Phoenix AZ, US
Nagaraja Rudrapatna - Chandler AZ, US

Assignee:

HONEYWELL INTERNATIONAL INC. - Morristown NJ

International Classification:

F02C 7/12

US Classification:

60752

Abstract:

A gas turbine engine combustor is provided. An inner liner has an upstream end and a downstream end and extends in an axial direction between the upstream and downstream ends. A dual wall outer liner has a hot wall, a cold wall at least partially surrounding the hot wall, an upstream end, and a downstream end. The outer liner extends in the axial direction between the upstream and downstream ends. A dome assembly is coupled between the upstream ends of the inner and outer liners to define a combustion chamber between the inner liner and the hot wall of the outer liner. Effusion cooling holes are disposed in the hot wall, including a first row disposed at a tangential angle of between about 70 and about 90 and a second row disposed at a tangential angle of between about 0 and about 20.

US Patent:

20110185739, Aug 4, 2011

Filed:

Jan 29, 2010

Appl. No.:

12/696688

Inventors:

Thomas J. Bronson - Mesa AZ, US
Nagaraja S. Rudrapatna - Chandler AZ, US

Assignee:

HONEYWELL INTERNATIONAL INC. - Morristown NJ

International Classification:

F02C 7/18

US Classification:

60755, 60752

Abstract:

A combustor for a turbine engine includes a hot wall and a cold wall forming a dual walled liner and a liner cavity with the hot wall. The cold wall defines a plurality of impingement cooling holes configured to deliver an impingement cooling flow. A first downstream end terminates the hot wall and is configured to receive the impingement cooling flow from the plurality of impingement cooling holes, and a second downstream end terminates the cold wall and is longer in a generally downstream direction than the first downstream end. A combustion chamber is formed with the dual walled liner and the liner and faces an opposite side of the hot wall relative to the combustion chamber. The combustion chamber has a longitudinal axis and is configured to receive an air-fuel mixture in the generally downstream direction along the longitudinal axis.