The stator and rotor blade hub sections designed for a high pressure turbine stage were studied in detail for their aerodynamic and heat transfer characteristics . The profile sections were tested in the National Aeronautical Laboratory Cascade Tunnels over a range of exit flow Mach numbers . The flow field and heat transfer characteristics of the cascades were also code based on Denton's method and the boundary layer code incorporating K- E turbulence model. The results indicated that there was a scope for improving the blade profile sections for high Mach number applications
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