Enhancement of Film Cooling Performance Using a Shaped Film Cooling Hole with Compound Angle Injection.

Simulation of Film Cooling Enhancement with Mist Injection

Cooling of gas turbine hot section components such as combustor liners, combustor transition pieces, turbine vanes (nozzles) and blades (buckets) is a critical task for improving the life and reliability of hotsection components. Conventional cooling techniques using air-film cooling, impingement jet cooling, and turbulators have significantly contributed to cooling enhancements in the past. Ho...

Film Cooling Measurements for Novel Hole Configurations

The effect of film cooling slot exit area and shape is studied. Detailed heat transfer coefficient and film effectiveness measurements are obtained simultaneously using a single transient IR thermography technique. Two designs with a crescent shaped exit and a slot exit are considered. The results show that the crescent shaped exit provides significantly higher film cooling effectiveness than t...

An Experimental Study of Momentum-Preserving Shaped Holes for Film Cooling Using PSP and PIV

An experimental investigation was conducted to study the performance of film cooling injection from a cylindrical hole and a “W-shaped” hole. A Pressure Sensitive Paint (PSP) technique was used to map the spatial distribution of film cooling effectiveness on the surface of the test plate based on a mass-transfer analogy. The effects of mass flux ratio and density ratio on film cooling effective...

Endwall Film-Cooling in Axial Flow Turbines

Evolution Strategies for Film Cooling Optimization

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