First stage, nozzle guide vanes and accompanying endwalls are extensively cooled by the use of film cooling through discrete holes and leakage flow from the combustor-turbine interface gap. While there are cooling benefits from the interface gap, it is generally not considered as part of the cooling scheme. This paper reports on the effects of the position and orientation of a two-dimensional slot on the cooling performance of a nozzle guide vane endwall. In addition to surface thermal measurements, time-resolved, digital particle image velocimetry (TRDPIV) measurements were performed at the vane stagnation plane. Two slot orientations, 90 deg and 45 deg, and three streamwise positions were studied. Effectiveness results indicate a significant increase in area averaged effectiveness for the 45 deg slot relative to the 90 deg orientation. Flowfield measurements show dramatic differences in the horseshoe vortex formation.
Effects of Orientation and Position of the Combustor-Turbine Interface on the Cooling of a Vane Endwall
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Thrift, A. A., Thole, K. A., and Hada, S. (September 4, 2012). "Effects of Orientation and Position of the Combustor-Turbine Interface on the Cooling of a Vane Endwall." ASME. J. Turbomach. November 2012; 134(6): 061019. https://doi.org/10.1115/1.4004817
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