Development of Low-Loss Supersonic Turbine Nozzle with Cooling-Capable Thick Trailing Edge

Abstract

In this study, we searched for the characteristics of airfoils with low loss coefficient in supersonic regimes using a three-dimensional automatic optimization method. Based on those characteristics, we redesigned the airfoil and developed a supersonic turbine nozzle with low loss coefficient and cooling-capable thick trailing edge. In analysis, loss coefficient of nozzle finally obtained in this study was improved by 25.9% in comparison with baseline nozzle.