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Mid-section of a can-annular gas turbine engine with a radial air flow discharged from the compressor section

United States Patent

October 25, 2016
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 midframe portion (213) of a gas turbine engine (210) is presented, and includes a compressor section (212) configured to discharge an air flow (211) directed in a radial direction from an outlet of the compressor section (212). Additionally, the midframe portion (213) includes a manifold (214) to directly couple the air flow (211) from the compressor section (212) outlet to an inlet of a respective combustor head (218) of the midframe portion (213).
Little; David A. (Chuluota, FL), McQuiggan; Gerard (Orlando, FL), Wasdell; David L. (Winter Park, FL)
13/ 408,147
February 29, 2012
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.