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METHOD AND SYSTEM TO REDUCE VANE SWIRL ANGLE IN A GAS TURBINE ENGINE

United States Patent Application

20100326079
A1
View the Complete Application at the US Patent & Trademark Office
A fuel nozzle assembly includes a swirler assembly having an inlet end, an outlet end, a shroud inner surface and a hub outer surface. The inner surface has a first diameter adjacent to the inlet end and a second diameter adjacent to the outlet end defining a differential diameter ratio. A plurality of vanes are coupled to the swirler assembly and extend between the shroud inner surface and the hub outer surface. The vanes have a pair of opposing sidewalls joined at a leading edge and at an axially-spaced trailing edge, and a first height adjacent to the leading edge and a second height adjacent to the trailing edge. The first height and the second height define a differential height ratio, wherein the differential diameter ratio, the differential height ratio, or both are configured to provide convergent flow through the fuel nozzle.
Zuo, Baifang (Simpsonville, SC), Ziminsky, Willy Steve (Simpsonville, SC), Lacy, Benjamin Paul (Greer, SC), Felling, David Kenton (Greenville, SC)
12/ 491,393
June 25, 2009
STATEMENT REGARDING FEDERALLY SPONSORED RESEARCH & DEVELOPMENT [0001] This invention was made with Government support under DE-FC26-05NT42643 awarded by the Department of Energy ("DOE"). The Government has certain rights in this invention.