Boundary Layer Transition Prediction on Planar Turbine Cascade Using Temperature-Sensitive Paint and Numerical Simulation

Advanced measurement technology on boundary layer transition is an effective means to study the flow mechanism and performance of cascade. In this research, investigate transonic VKI-RG turbine cascade, a noncontact technique named temperature-sensitive paint (TSP) that capable quantitatively measuring surface temperature model used. Under conditions outlet Mach number (Ma2) = 0.4, 1.03, 1.2, transitional location cascade accurately measured by TSP technique. Moreover, numerical planar was conducted with (Ma) attack angle (α). The results show moved forward increase in Ma2 α at < 1; otherwise, backward increasing (Ma2 > 1). Lastly, strong adverse pressure gradient formed behind shock wave, which led beginning transition.