Kevin R Spence

US Patent:

20190178495, Jun 13, 2019

Filed:

Feb 20, 2019

Appl. No.:

16/280173

Inventors:

- Orlandp FL, US
Richard L. Thackway - Oviedo FL, US
Stephen A. Ramier - Fredericton, CA
Vinayak V. Barve - Cumming GA, US
Khalil Farid Abou-Jaoude - Winter Springs FL, US
Daniel W. Garan - Chuluota FL, US
David P. Holzapfel - Charlotte NC, US
Kevin J. Spence - Jupiter FL, US
Joseph Scott Markovitz - Sanford FL, US
Blake R. Cotten - Orlando FL, US
Urmi B. Dave - Oviedo FL, US
Vaidyanathan Krishnan - Charlotte NC, US
Michael C. Escandon - Oviedo FL, US

International Classification:

F23R 3/00
F23R 3/06
F23R 3/16
F23R 3/28
F23R 3/36
F23R 3/48
F02C 3/04
F01D 9/02

Abstract:

An improved combustion section for a gas turbine engine is disclosed. A fuel nozzle includes new features which provide improved injection patterns of oil fuel and cooling water, resulting in better control of combustion gas temperature and NOx emissions, and eliminated impingement of cooling water on walls of the combustor. A new combustor includes a plate-fin design which provides improved cooling, while the combustor also makes more efficient use of available cooling air and has an improved component life. A new transition component has a smoother shape which reduces stagnation of combustion gas flow and impingement of combustion gas on transition component walls, improved materials and localized thickness increases for better durability, and improved cooling features for more efficient usage of cooling air.

US Patent:

20170227228, Aug 10, 2017

Filed:

Sep 5, 2014

Appl. No.:

15/502638

Inventors:

- München, DE
Richard L. Thackway - Oviedo FL, US
David P. Holzapfel - Charlotte NC, US
Stephen A. Ramier - Fredericton, New Brunswick, CA
Charalambos Polyzopoulos - Orlando FL, US
Kevin J. Spence - Winter Springs FL, US
Joseph Scott Markovitz - Sanford FL, US

Assignee:

SIEMENS AKTIENGESELLSCHAFT - Muenchen

International Classification:

F23R 3/48
F23R 3/46

Abstract:

A cross-flame duct () for connecting adjacent combustors () together in a gas turbine to guard against flameout conditions within the combustors (), whereby the cross-flame duct () may include first and second ducts () forming a slip joint to prevent stress from developing within the cross-flame duct () is disclosed. The cross-flame duct () remains flexible during turbine operation due to the slip joint, thereby preventing damaging thermal and mechanical stresses from developing within the cross-flame duct () and enhancing the useful life of the cross-flame duct () and associated components. The first and second ducts () may also include cooling chambers () positioned between outer sleeves () and inner housings () and maintained with one or more standoffs () to reduce thermal stress and gradients or prevent material loss due to overheating or burning. The cooling chambers () may be supplied with cooling fluids via one or more fluid ports () extending through the outer sleeves () enabling air to flow through the cooling chambers () and into the combustors ().

US Patent:

20160348911, Dec 1, 2016

Filed:

Dec 10, 2014

Appl. No.:

14/566125

Inventors:

- Orlando FL, US
Richard L. Thackway - Oviedo FL, US
Stephen A. Ramier - Fredericton, CA
Vinayak V. Barve - Oviedo FL, US
Khalil Farid Abou-Jaoude - Winter Springs FL, US
Daniel W. Garan - Chuluota FL, US
David P. Holzapfel - Oviedo FL, US
Kevin J. Spence - Winter Springs FL, US
Joseph Scott Markovitz - Sanford FL, US
Blake R. Cotten - Orlando FL, US
Urmi B. Dave - Charlotte NC, US
Vaidyanathan Krishnan - Chennai, IN
Michael C. Escandon - Oviedo FL, US

International Classification:

F23R 3/00
F23R 3/48
F02C 3/04

Abstract:

An improved combustion section for a gas turbine engine is disclosed. A fuel nozzle includes new features which provide improved injection patterns of oil fuel and cooling water, resulting in better control of combustion gas temperature and NOx emissions, and eliminated impingement of cooling water on walls of the combustor. A new combustor includes a plate-fin design which provides improved cooling, while the combustor also makes more efficient use of available cooling air and has an improved component life. A new transition component has a smoother shape which reduces stagnation of combustion gas flow and impingement of combustion gas on transition component walls, improved materials and localized thickness increases for better durability, and improved cooling features for more efficient usage of cooling air.

US Patent:

20140338332, Nov 20, 2014

Filed:

May 14, 2013

Appl. No.:

13/893441

Inventors:

Juan Enrique Portillo Bilbao - Oviedo FL, US
Rajesh Rajaram - Oviedo FL, US
Danning You - Shanghai, CN
Kevin J. Spence - Winter Springs FL, US

International Classification:

F23M 23/20

US Classification:

60725

Abstract:

An acoustically dampened gas turbine engine having a gas turbine engine combustor with an acoustic damping resonator system is disclosed. The acoustic damping resonator system may be formed from one or more resonators positioned within the gas turbine engine combustor at an outer housing forming a combustor basket and extending circumferentially within the combustor. The resonator may be positioned in a head region of the combustor basket. In one embodiment, the resonator may be positioned in close proximity to an intersection between the outer housing and an upstream wall defining at least a portion of the combustor. The acoustic damping resonator system may mitigate longitudinal mode dynamics thereby increasing an engine operating envelope and decreasing emissions.