This paper presents an experimental investigation of the film cooling performance of a New Hybrid Film Cooling Scheme using Thermochromic Liquid Crystal technique. The new scheme has been designed to improve the film cooling performance of gas turbine airfoils. The scheme includes two consecutive film hole configurations with interior bending. The cooling performance of the new scheme was analyzed across blowing ratios of 0.5, 1.0 and 1.5, at a density ratio of 0.94. The results showed that the new scheme enhanced the local and the laterally averaged film cooling performance in terms of effectiveness, and net heat flux reduction in compared to other film hole configurations. The bending effect of the new scheme throttled the secondary flow causing it to spread widely over the downstream surfaces, hence enhancing the film cooling performance at low and high blowing ratios. The hybrid scheme provided an average heat transfer ratio near unity over the downstream surfaces at low and high blowing ratios.
Experimental investigation of liquid film cooling in hypersonic flow
