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GAS FLOW PATH FOR A GAS TURBINE ENGINE

United States Patent Application

20150233582
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 duct arrangement in a can annular gas turbine engine. The gas turbine engine has a gas delivery structure for delivering gases from a plurality of combustors to an annular chamber that extends circumferentially and is oriented concentric to a gas turbine engine longitudinal axis for delivering the gas flow to a first row of blades A gas flow path is formed by the duct arrangement between a respective combustor and the annular chamber for conveying gases from each combustor to the first row of turbine blades The duct arrangement includes at least one straight section having a centerline that is misaligned with a centerline of the combustor.
Montgomery, Matthew D. (Jupiter, FL), Charron, Richard C. (West Palm Beach, FL), Snyder, Gary D. (Jupiter, FL), Pankey, William W. (Palm Beach Gardens, FL), Mayer, Clinton A. (Jupiter, FL), Hettinger, Benjamin G. (Jupiter, FL)
SIEMENS ENERGY, INC. (Orlando FL)
14/ 185,352
February 20, 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.