涡轮叶片吸力面上收敛缝形孔气膜冷却效率的数值研究  

Numerical Investigation on Film Cooling Effectiveness of Converging Slot Hole at Turbine Blade Suction Surface

作　　者：姚玉[1] 张靖周[1] 何飞 郭文[3] 

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016 [2]洪都航空工业集团,江西南昌330024 [3]中国燃气涡轮研究院,四川成都610500

出　　处：《航空学报》2010年第6期1115-1120,共6页Acta Aeronautica et Astronautica Sinica

基　　金：航空基础科学基金(03C52019)

摘　　要：运用RNG湍流模型对叶片吸力面开设收敛缝形孔的冷却特性进行了数值模拟,分析在叶栅通道主流入口雷诺数Re=4×105~6×105和二次流吹风比M=0.5~3.0范围内,沿吸力面3个典型弦向位置处（分别对应叶栅通道喉部上游、喉部和喉部下游）开设收敛缝形孔对气膜冷却效果的影响。计算结果表明：各位置处收敛缝形孔吸力面的冷却效率随着吹风比和主流入口雷诺数的增大而逐渐升高;与圆形孔相比,各位置处收敛缝形孔沿流向的冷却效率均得到有效改善,且在展向上的分布较均匀;在相同的主流入口雷诺数和二次流吹风比下,位于喉部上游位置的收敛缝形孔冷却效率大都高于其他位置。The film cooling characteristics of a converging slot hole on the blade suction surface of a turbine are numerically investigated using the RNG turbulence model under different turbine cascade inlet Reynolds numbers（ranging from 4×105 to 6×105） and blowing ratios（ranging from 0.5 to 3.0）.The influence of the location of the converging slot hole at the blade suction surface（corresponding respectively to the upstream of the throat,the cascade throat and the downstream of the throat） on film cooling effectiveness is investigated.The results show that the converging slot hole cooling effectiveness in different locations all increases with the increase of the mainstream Reynolds number and coolant blowing ratio.Compared with the cylindrical hole,the converging slot hole cooling effectiveness is improved obviously and more uniform in lateral variation in all locations.Under the same condition,the cooling effectiveness of the converging slot hole at the upstream of the throat is nearly always higher than that in the other locations.

关 键 词：收敛缝形孔 气膜冷却 冷却效率 吸力面 涡轮叶片 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]