Characteristics Downstream of Turbomachine Blade Rows in Terms of

The author has written a concise summary of the com-putational/experimental techniques that are presently being used at NASA Lewis to evaluate subsonic/transonic turbine stage performance. The references cited indicate that ex-tensive analytical and experimental research has been con-ducted in the area of turbine aerodynamic design. In par-ticular, stators and contoured stators have been investigated for total-to-static pressure ratios in the range of 1.20-2.1. Reaction rotors have been considered for a total-to-static pressure range of 1.87-2.06. The aftermix or mixed-out uniform exit conditions hav