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Title: Cooling system for fuel nozzles within combustor in a turbine engine

Abstract

A cooling system for a fuel system in a turbine engine that is usable to cool a fuel nozzle is disclosed. The cooling system may include one or more cooling system housings positioned around the fuel nozzle, such that the cooling system housing forms a cooling chamber defined at least partially by an inner surface of the cooling system housing and an outer surface of the fuel nozzle. The fuel nozzle may extend into a combustor chamber formed at least in part by a combustor housing. The fuel nozzle may include one or more fuel exhaust orifices with an opening in an outer surface of the fuel nozzle and configured to exhaust fluids unrestricted by the housing forming the cooling system cooling chamber. The cooling system may provide cooling fluids to cool the fuel nozzle within the cooling system cooling chamber regardless of whether the fuel nozzle is in use.

Inventors:
; ; ; ;
Publication Date:
Research Org.:
Siemens Energy, Inc., Orlando, FL (United States)
Sponsoring Org.:
USDOE
OSTI Identifier:
1568425
Patent Number(s):
10,309,655
Application Number:
15/500,954
Assignee:
Siemens Energy, Inc. (Orlando, FL)
DOE Contract Number:  
FC26-05NT42644
Resource Type:
Patent
Resource Relation:
Patent File Date: 08/26/2014
Country of Publication:
United States
Language:
English
Subject:
33 ADVANCED PROPULSION SYSTEMS

Citation Formats

Laster, Walter Ray, Martin, Scott M., Portillo Bilbao, Juan Enrique, Hardes, Jacob William, and Fox, Timothy A. Cooling system for fuel nozzles within combustor in a turbine engine. United States: N. p., 2019. Web.
Laster, Walter Ray, Martin, Scott M., Portillo Bilbao, Juan Enrique, Hardes, Jacob William, & Fox, Timothy A. Cooling system for fuel nozzles within combustor in a turbine engine. United States.
Laster, Walter Ray, Martin, Scott M., Portillo Bilbao, Juan Enrique, Hardes, Jacob William, and Fox, Timothy A. 2019. "Cooling system for fuel nozzles within combustor in a turbine engine". United States. https://www.osti.gov/servlets/purl/1568425.
@article{osti_1568425,
title = {Cooling system for fuel nozzles within combustor in a turbine engine},
author = {Laster, Walter Ray and Martin, Scott M. and Portillo Bilbao, Juan Enrique and Hardes, Jacob William and Fox, Timothy A.},
abstractNote = {A cooling system for a fuel system in a turbine engine that is usable to cool a fuel nozzle is disclosed. The cooling system may include one or more cooling system housings positioned around the fuel nozzle, such that the cooling system housing forms a cooling chamber defined at least partially by an inner surface of the cooling system housing and an outer surface of the fuel nozzle. The fuel nozzle may extend into a combustor chamber formed at least in part by a combustor housing. The fuel nozzle may include one or more fuel exhaust orifices with an opening in an outer surface of the fuel nozzle and configured to exhaust fluids unrestricted by the housing forming the cooling system cooling chamber. The cooling system may provide cooling fluids to cool the fuel nozzle within the cooling system cooling chamber regardless of whether the fuel nozzle is in use.},
doi = {},
url = {https://www.osti.gov/biblio/1568425}, journal = {},
number = ,
volume = ,
place = {United States},
year = {2019},
month = {6}
}

Works referenced in this record:

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patent, January 2017


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patent, August 2005


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patent, June 2015


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patent, December 2015


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patent, March 2014


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patent, June 1983


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patent, July 2010


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patent, January 1997


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patent, August 1978


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patent, March 2009


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patent, August 2013


Simplex airblade fuel injection method
patent, May 1992


Mixer having multiple swirlers
patent, April 2002


Air fuel mixer for gas turbine combustor
patent, November 2000