External heat transfer study on a HP turbine rotor blade
Abstract
An experimental investigation of the effects of Mach number, Reynolds numbers and free stream turbulence intensity on the heat transfer performance of a high pressure gas turbine rotor blade in a stationary linear cascade arrangement is described. This study was undertaken in the von Karman Institute short duration isentropic compression tube facility. The tests were performed for outlet Mach numbers ranging between 0.7 and 1, whereas the outlet Reynolds number was varied between 500,000 and 1,500,000; free stream turbulence levels between 1% and nearly 8% were considered. The experimental results were compared with boundary layer predictions provided by a finite difference program (STAN5), which solves the simplified, two dimensional, steady Navier-Stokes equations.
- Publication:
-
In AGARD Heat Transfer and Cooling in Gas Turbines 12 p (SEE N86-29823 21-07
- Pub Date:
- September 1985
- Bibcode:
- 1985htcg.agarR....A
- Keywords:
-
- Air Cooling;
- Gas Turbines;
- Heat Transfer;
- Mach Number;
- Reynolds Number;
- Rotor Blades (Turbomachinery);
- Turbine Blades;
- Turbulence Effects;
- Boundary Layer Transition;
- Boundary Layers;
- Finite Difference Theory;
- Flow Velocity;
- High Pressure;
- Velocity Distribution;
- Fluid Mechanics and Heat Transfer