Several problem areas associated with air-cooling of small turbine blades and vanes are identified. These problem areas include the leading edge cooling by film and impingement cooling, comparison of several configurations for trailing edge cooling, effects of Mach number on blade surface heat transfer, effects of film cooling on the aerodynamic performances of turbine cascades, the method of data correlation for the application of heat transfer data taken with low temperature, low pressure rig tests to high temperature, high pressure conditions. Experimental data are presented for each discussed area. The description of design and experimental data of one of the experimental cooled blades and vanes are presented.

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