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DUAL OUTLET NOZZLE FOR A SECONDARY FUEL STAGE OF A COMBUSTOR OF A GAS TURBINE ENGINE

United States Patent Application

20150276226
A1
View the Complete Application at the US Patent & Trademark Office
U.S. Department of Energy - Visit the Office of the Assistant General Counsel for Technology Transfer & Intellectual Property Website
A secondary fuel stage (14) of a combustor of a gas turbine engine. The combustor has a main combustion zone (43) upstream of the secondary fuel stage to ignite working gas The secondary fuel stage includes a nozzle (18) with dual outlets (20, 22) oriented with a circumferential component to inject an air-fuel mixture (24) into the combustor. The nozzle is effective to entrain the air-fuel mixture with the working gas (44) such that a peak temperature (46) of the working gas at a location downstream of the secondary fuel stage is less than a peak temperature (50) of working gas if the air-fuel mixture were injected into the combustor with a single outlet nozzle (118).
Laster, Walter R. (Oviedo, FL), Martin, Scott M. (Daytona Beach, FL), Portillo Bilbao, Juan Enrique (Oviedo, FL), Hardes, Jacob (Charlotte, NC), Fox, Timothy A. (Hamilton, CA)
Siemens Energy, Inc. (Orlando FL)
14/ 228,883
March 28, 2014
STATEMENT REGARDING FEDERALLY SPONSORED DEVELOPMENT [0001] Development for this invention was supported in part by Contract No DE-FC26-05NT42644, awarded by the United States Department of Energy. Accordingly, the United States Government may have certain rights in this invention