In this paper we establish a benchmark data set of a generic high-pressure turbine vane generated by direct numerical simulation (DNS) to resolve fully the flow. The test conditions for this case are a Reynolds number of 0.57 million and an exit Mach number of 0.9, which is representative of a modern transonic high-pressure turbine vane. In this study we first compare the simulation results with previously published experimental data. We then investigate how turbulence affects the surface flow physics and heat transfer. An analysis of the development of loss through the vane passage is also performed. The results indicate that free-stream turbulence tends to induce streaks within the near wall flow, which augment the surface heat transfer. Turbulent breakdown is observed over the late suction surface, and this occurs via the growth of two-dimensional Kelvin-Helmholtz spanwise roll-ups, which then develop into lambda vortices creating large local peaks in the surface heat transfer. Turbulent dissipation is found to significantly increase losses within the trailing-edge region of the vane.
Direct Numerical Simulations of a High Pressure Turbine Vane
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Wheeler, APS, Sandberg, RD, Sandham, ND, Pichler, R, Michelassi, V, & Laskowski, G. "Direct Numerical Simulations of a High Pressure Turbine Vane." Proceedings of the ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. Volume 2A: Turbomachinery. Montreal, Quebec, Canada. June 15–19, 2015. V02AT38A027. ASME. https://doi.org/10.1115/GT2015-43133
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