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- W68098377 abstract "Film cooling with ejection of the coolant from a row of holes is the only practical way to apply this cooling method to gas turbine blades. A literature survey shows that information on this type of cooling is very limited. Measurements of the adiabatic wall effectiveness and the heat transfer coefficient on a flat plate downstream of a row of ejection holes are described. The effect of the principal flow parameters is studied for ejection of hot air into a cold air main flow. Laterally averaged values are measured for an ejection angle of 35° and a spacing diameter ratio of 3. Ejection at a stagnation point is investigated also.The main test conditions, such as main flow Mach numbers, pressure gradients and boundary layer properties are determined according to experiments on a cascade of typical turbine blade profiles. Application of the results to film cooled gas turbine blades is, therefore, possible. It is found that the main flow Mach number and Reynolds number in the range covered by the tests have no measurable effect on the adiabatic wall effectiveness and the heat transfer coefficient. The importance of the mass velocity ratio on the film cooling parameters is confirmed. The effect of main flow pressure gradient and boundary layer thickness is found to be of the same order as the effect of the mass velocity ratio. A strong favorable pressure gradient or a thick boundary layer can reduce the effectiveness by a factor of two." @default.
- W68098377 created "2016-06-24" @default.
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- W68098377 date "1973-03-01" @default.
- W68098377 modified "2023-09-23" @default.
- W68098377 title "Film cooling with ejection from a row of inclined circular holes: An experimental study for the application to gas turbine blades" @default.
- W68098377 hasPublicationYear "1973" @default.
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