The current demands for high-performance gas turbine engines can be reached by raising combustion temperatures to increase power output. High combustion temperatures create a harsh environment that leads to the consideration of the durability of the combustor and turbine sections. This paper presents a computational study of a flow field that is representative of what occurs in a combustor and how that flow field convects through the first downstream stator vane. The results of this study indicate that the development of the secondary flow field in the turbine is highly dependent on the incoming total pressure profile. The endwall heat transfer is also found to depend strongly on the secondary flow field.
Flow Field Computations of Combustor-Turbine Interactions Relevant to a Gas Turbine Engine
Contributed by the International Gas Turbine Institute and presented at the International Gas Turbine and Aeroengine Congress and Exhibition, Atlanta, GA, June 16–19, 2003. Manuscript received by the IGTI December 2002; final revision March 2003. Paper No. 2003-GT-38253. Review Chair: H. R. Simmons.
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Stitzel, S., and Thole , K. A. (March 26, 2004). "Flow Field Computations of Combustor-Turbine Interactions Relevant to a Gas Turbine Engine ." ASME. J. Turbomach. January 2004; 126(1): 122–129. https://doi.org/10.1115/1.1625691
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