Simulations of Shock/Boundary-Layer Interactions Over Highly Loaded Turbine Blades

Transonic viscous flow over highly loaded turbine blades, where the interaction of a shock wave and a boundary layer often leads to extremely complicated flow phenomena, has been studied numerically in this paper. A Modified Implicit Flux Vector Splitting solver of the Navier-Stokes equations, which has been well established though combining a unique implicit formulation with a Flux Vector Splitting, has been extended to simulate a transonic cascade flow. A low Reynolds number k-ε turbulence model, with the compressibility effect considered, and a transition model have been implemented to predict heat transfer, flow patterns in the high loaded transonic turbine vanes and turbine vanes and blades. Numerical investigations show it has obvious superiority in terms of accuracy, robustness, convergence and computing time.