槽缝射流对高负荷涡轮非轴对称端壁冷却性能的影响研究

Based on endwall static pressure distribution contouring method，the difference of cooling performance about global and local non-axisymmetric endwall contouring was studied in this research for a high load turbine with purge flow. The effects of incidence angles and slot structures on endwall cooling characteristics of non-axisymmetric contouring were also revealed. The results show that the non-axisymmetric endwall contouring can alter the aerodynamic and cooling performance simultaneously. By inhibiting the secondary flow，the non-axisymmetric endwall contouring can reduce the total cascade pressure loss coefficient 0.364%. The effective area covered by the coolant can increase by 13.57% compared to a flat endwall，but the laterally averaged film effectiveness is decreased. The non-axisymmetric endwall contouring could improve the protection effect of large angle purge flow. Under the work of tangent circle slot structure，coolant coverage area increases by 11.51% compared with flat endwall.