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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 Application

*** PATENT GRANTED ***
20130224009
9,476,355
A1
View the Complete Application at the US Patent & Trademark Office
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 [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.