Skip to Content
Find More Like This
Return to Search

Gas flow path for a gas turbine engine

United States Patent

9,593,853
March 14, 2017
View the Complete Patent 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 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.