Closure to “Discussion of ‘Heat Transfer With Film Cooling Near Nontangential Injection Slots’” (1968, ASME J. Eng. Power, 90, pp. 162–163)

Abstract

which cannot be verified with (he present test facility. However, this generalization seems justified by previous film cooling studies.Depending on the mainstream temperature, the available coolant temperature, and the desired surface temperature, together with the total thermal environment of the part to be cooled, practically any value of 6* could conceivably be of interest. However, in gas turbine applications, the film-air temperature depends primarily 011 the compressor pressure ratio, and the range of interest of 8* will probably be: