Effectiveness of film cooling applied to gas-turbine nozzle guide vanes
Abstract
In the experiments described, a gas-turbine vane containing a cooling-air baffle was used to study the influence of a pressure gradient on the effectiveness of film cooling. The wall temperature of the vane was measured at its convex and concave sides at an injected-air temperature between 1150 and 1200 K and a trailing-edge Mach number of 0.4 to 0.65. The pressure distribution over the vane profile was measured for various pressure gradients at a gas-flow temperature of 340 K. The results obtained are plotted and discussed. They are shown to be in good agreement with the results obtained by Lander, Fish, and Mikio Suo (1972).
- Publication:
-
Teploenergetika
- Pub Date:
- January 1978
- Bibcode:
- 1978Teplo........9B
- Keywords:
-
- Film Cooling;
- Gas Turbine Engines;
- Guide Vanes;
- Nozzle Flow;
- System Effectiveness;
- Air Flow;
- Leading Edges;
- Pressure Gradients;
- Wall Temperature;
- Fluid Mechanics and Heat Transfer