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COOLING SYSTEM FOR FUEL NOZZLES WITHIN COMBUSTOR IN A TURBINE ENGINE

United States Patent Application

20170219212
A1
View the Complete Application at the US Patent & Trademark Office
A cooling system (10) for a fuel system in a turbine engine (14) that is usable to cool a fuel nozzle (16) is disclosed. The cooling system (10) may include one or more cooling system housings (18) positioned around the fuel nozzle (16), such that the cooling system housing (18) forms a cooling chamber (20) defined at least partially by an inner surface (22) of the cooling system housing (18) and an outer surface (24) of the fuel nozzle (16). The fuel nozzle (16) may extend into a combustor chamber (26) formed at least in part by a combustor housing (32). The fuel nozzle (16) may include one or more fuel exhaust orifices (28) with an opening (30) in an outer surface (24) of the fuel nozzle (16) and configured to exhaust fluids unrestricted by the housing (18) forming the cooling system cooling chamber (20). The cooling system (10) may provide cooling fluids to cool the fuel nozzle (16) within the cooling system cooling chamber (20) regardless of whether the fuel nozzle (16) is in use.
Laster, Walter Ray (Oviedo, FL), Martin, Scott M. (Daytona Beach, FL), Portillo Bilbao, Juan Enrique (Oviedo, FL), Hardes, Jacob William (Charlotte, NC), Fox, Timothy A. (Hamilton, Ontario, CA)
15/ 500,954
August 26, 2014
STATEMENT REGARDING FEDERALLY SPONSORED RESEARCH OR DEVELOPMENT [0001] Development of this invention was supported in part by the United States Department of Energy, Advanced Turbine Development Program, Contract No. DE-FC26-05NT42644. Accordingly, the United States Government may have certain rights in this invention.