The simulating experiments have been completed to research the characteristics of impingement cooling in midchord region of turbine blade in the condiltons of given geometric para-meter of jet array

initial crossflow and pressure ratios of film cooling exhaust.Comparative experiments have been made between curvilinear and flate plate impinged surfaces

and impinged surfaces with and without chordwise fin.Moreover

the thermal patterns from liquid crystal indication show that the jet hole arrangement and distance between cooled surface and jet plate affect the heat transfer distributions for jet array impingement.Finally

the effects of the cooling air axially injected into guide tube on radial jets flow have also been determined by measurements.