High-Fidelity Simulations of a High-Pressure Turbine Vane Subject to Large Disturbances: Effect of Exit Mach Number on Losses

Abstract We report on a series of highly resolved large-eddy simulations the LS89 high-pressure turbine (HPT) vane, varying exit Mach number between Ma = 0.7 and 1.1. In order to accurately resolve blade boundary layers enforce pitchwise periodicity, we for first time use an overset mesh method, which consists O-type grid around overlapping with background H-type grid. The were conducted either synthetic inlet turbulence condition or including upstream bars. A quantitative comparison shows that computationally more efficient method is able reproduce characteristics further perform detailed analysis flow fields, showing significantly changes efficiency by affecting suction-side transition, layer profiles, wake mixing. particular, 1.1 case includes strong shock interacts trailing edge, causing increased complexity field. our recently developed entropy loss (Zhao Sandberg, 2019, “Using New Entropy Loss Analysis Assess Accuracy RANS Predictions HPT Vane,” ASME Turbo Expo 2019: Turbomachinery Technical Conference Exposition, Paper No. GT2019-90126) decompose overall into different source terms identify regions dominate generation. Comparing cases, conclude main mechanism extra generation in shock-related pressure gradient interacting turbulent wake, resulting significant production extensive viscous dissipation.