An Experimental Study on Aerodynamic Performance of Turbine Nozzle Guide Vanes With Trailing Edge Span Wise Ejection

Abstract

The present experimental study is to examine the influence of trailingedge coolant ejection with the spanwise inclination on the aerodynamic loss of turbine nozzle guide vanes. This study uses a cascade of five vanes located in the test section of a lowspeed wind tunnel. The vanes have the profile of highpressure nozzle guide vanes, and the central vane is equipped with the internal cooling and the trailingedge coolant ejection. The coolant is ejected through trailingedge slots that are inclined in the spanwise direction at angles varying from 0 deg to 45 deg in 15 deg increments. The results indicate an optimum ejection rate, at which the aerodynamic loss is minimum. There is a little variation in loss as the spanwise inclination is varied when the ratio of coolant to mainstream gas mass flow rate is less than 1.5%. For higher coolant flow rates, however, the loss increases with increases in the spanwise ejection angle.