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MID-SECTION OF A CAN-ANNULAR GAS TURBINE ENGINE TO INTRODUCE A RADIAL VELOCITY COMPONENT INTO AN AIR FLOW DISCHARGED FROM A COMPRESSOR OF THE MID-SECTION

United States Patent Application

20130224007
A1
View the Complete Application at the US Patent & Trademark Office
A midframe portion (113) of a gas turbine engine (110) is provided, including a compressor section (112) with a last stage blade (124). The compressor section (112) is configured to introduce a radial velocity component into an air flow (111) such that the air flow is discharged from the compressor section (112) at a mixed direction based on a combined longitudinal velocity component and radial velocity component. The midframe portion (113) further includes a manifold (121) to directly couple the air flow from an outlet of the compressor section (112) to an inlet of a respective combustor head (118) of the gas turbine engine (110).
Rodriguez, Jose L. (Lake Mary, FL)
13/ 407,987
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.