Philip James Kirsopp

US Patent:

8291706, Oct 23, 2012

Filed:

Jun 11, 2009

Appl. No.:

12/482516

Inventors:

Keith M. Tanner - Colchester CT, US
Philip J. Kirsopp - Lebanon CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F02C 1/00
F02G 3/00

US Classification:

60740, 60737, 60800, 60796, 2395871

Abstract:

A bearing plate assembly for a turbine engine fuel injector includes a bearing plate , with an opening bordered by a race. A swivel ball nests inside the race and is rotatable relative thereto. A lock, which may be a tip bushing resists disengagement of the swivel ball from the race. A fuel injector nozzle extends through an opening in the swivel ball. During engine operation, the ball can swivel inside the race to accommodate rotational movement of the nozzle about lateral and radial axes.

US Patent:

20060207258, Sep 21, 2006

Filed:

Mar 21, 2005

Appl. No.:

11/085493

Inventors:

Keith Tanner - Colchester CT, US
Philip Kirsopp - Lebanon CT, US

International Classification:

F23R 3/14

US Classification:

060748000, 060740000

Abstract:

A bearing plate assembly for a turbine engine fuel injector includes a bearing plate , with an opening bordered by a race . A swivel ball nests inside the race and is rotatable relative thereto. A lock, which may be a tip bushing resists disengagement of the swivel ball from the race. A fuel injector nozzle extends through an opening in the swivel ball. During engine operation, the ball can swivel inside the race to accommodate rotational movement of the nozzle about lateral and radial axes.

US Patent:

20110052381, Mar 3, 2011

Filed:

Aug 28, 2009

Appl. No.:

12/549693

Inventors:

James B. Hoke - Tolland CT, US
Philip J. Kirsopp - Lebanon CT, US

International Classification:

F01D 9/04

US Classification:

415191

Abstract:

A turbine vane downstream of a combustor section includes an arcuate outer vane platform defined about an axis, the arcuate outer vane platform includes a segment of the arcuate outer vane platform along the axis which follows an outer combustor liner panel structure and an arcuate inner vane platform defined about the axis, the arcuate inner vane platform includes a segment of the arcuate inner vane platform along the axis which follows an inner combustor liner panel structure.

US Patent:

20110126543, Jun 2, 2011

Filed:

Nov 30, 2009

Appl. No.:

12/627528

Inventors:

Philip J. Kirsopp - Lebanon CT, US
Aaron J. Dornback - Wethersfield CT, US
James B. Hoke - Tolland CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F02C 7/22
F02C 3/14

US Classification:

60742, 60754

Abstract:

A combustor module for a gas turbine engine is provided that includes a first annular liner assembly extending along a longitudinal axis of the engine. The first annular liner assembly includes a first annular support shell and a plurality of first heat shield panels coupled to the first annular support shell. The first heat shield panels form a segmented ring defining a plurality of first axial seams therebetween. The combustor module further includes a bulkhead coupled to the first annular liner assembly. The bulkhead provides a plurality of fuel nozzles for passing a first mass flow comprising fuel and air. The combustor module further includes a second annular liner assembly coupled to the bulkhead. The second annular liner assembly is in spaced-apart generally coaxial relationship from the first annular liner assembly by a channel height H. The second annular liner assembly includes an air admittance hole having a mean diameter D extending along a hole axis. The hole axis is offset from the first axial seam defined by the first heat shield panels.

US Patent:

20130341912, Dec 26, 2013

Filed:

Jun 11, 2009

Appl. No.:

12/482513

Inventors:

Keith M. Tanner - Colchester CT, US
Philip J. Kirsopp - Lebanon CT, US

International Classification:

F23R 3/28
F16L 27/08

US Classification:

285272, 384 2

Abstract:

A bearing plate assembly for a turbine engine fuel injector includes a bearing plate with an opening bordered by a race A swivel ball nests inside the race and is rotatable relative thereto. A lock, which may be a tip bushing resists disengagement of the swivel ball from the race. A fuel injector nozzle extends through an opening in the swivel ball. During engine operation, the ball can swivel inside the race to accommodate rotational movement of the nozzle about lateral and radial axes.

US Patent:

20160195272, Jul 7, 2016

Filed:

Dec 16, 2015

Appl. No.:

14/971573

Inventors:

- Farmington CT, US
Philip J. Kirsopp - Lebanon CT, US
David A. Litton - West Hartford CT, US
Mark F. Zelesky - Bolton CT, US
Dennis M. Moura - South Windsor CT, US
Aaron S. Butler - Colchester CT, US

International Classification:

F23R 3/00
C23C 14/08
C23C 4/11
C23C 4/134
F02C 7/28
C23C 4/129
C23C 14/32
F01D 5/28
F01D 9/02
C23C 14/30
C23C 28/00

Abstract:

The present disclosure relates to methods for coating gas turbine engine components, such as combustor panels. In one embodiment, a method includes forming a first layer to a substrate to form a bond coat, and forming a second layer over the first layer. The second layer may be formed by a material having a thermal conductivity within the range of 4.45 to 30 Kcal/(m hoC). According to one or more embodiments, the first layer may be formed by at least one of a high velocity oxy-fuel (HVOF) source, an electric-arc source and low pressure plasma spraying. According to one or more embodiments, the second layer, and as a result a thermal barrier coating, may be formed by at least one of air plasma spraying, suspension plasma spraying, and electronic beam physical vapor deposition.