Effects of Localized Non-Gaussian Roughness on High-Pressure Turbine Aerothermal Performance: Convective Heat Transfer, Skin Friction, and the Reynolds' Analogy

Abstract

Compressible direct numerical simulations are conducted to investigate how surface roughness affects the aerothermal performance of a high-pressure turbine vane operating at an exit Reynolds number of 0.59 ×106 and exit Mach number of 0.92. The roughness under investigation here was synthesized with non-Gaussian statistical properties and an amplitude that varies over its chord length, representative of what truly occurs on an in-service vane. Particular attention is directed toward how systematically changing the axial extent of leading edge roughness affects convective heat transfer (Nusselt and Stanton numbers) and aerodynamic drag (skin friction coefficient) on the pressure and suction s..