生体模倣手法による航空エンジン用低圧タービン翼列の高効率化

(EFD・CFDによる新型後縁形状の提案)

抄録

Several types of trailing edge geometries of low-pressure turbine for aircraft are examined in this study. Steady research and development efforts have been made to improve the efficiency of low-pressure turbines, and recently, studies on reduc-ing the wake loss downstream of the blade trailing edge have been attracting attention for that purpose. However, most of those studies are based on numerical analysis only, and the actual effect of reducing blade wake loss has not been confirmed yet. In this study, several trailing edge models were proposed based on the previous studies and applied to a typical high-lift, low-pressure turbine cascade including the original geometry without geometry modification (called “base”). Experimental and numerical analyses were combined to provide a detailed discussion of the flow field.