导向器叶片尾缘厚度对涡轮性能影响研究  

Research of Stator Trailing Edge Thickness Effects on Turbine Performance

作　　者：石德永[1] 宋文艳[1] 浮强[1] 

机构地区：[1]西北工业大学动力与能源学院,陕西西安710072

出　　处：《机械设计与制造》2013年第11期102-104,108,共4页Machinery Design & Manufacture

摘　　要：某型低压涡轮导向器的冷却方式为"尾缘劈缝"冷却,叶片尾缘处的复杂结构降低了其制造精度。通过计算分析不同叶盆尾缘厚度D1和叶背尾缘厚度D2下的涡轮流场和性能,并与原型叶片计算结果进行了对比分析。研究结果表明:(1)尾缘厚度偏离原型叶片尾缘厚度,涡轮效率降低,涡轮效率的降低幅度与尾缘厚度的偏离程度成正比。(2)尾缘厚度的变化对涡轮功的影响较小。(3)尾缘厚度D1的变化对涡轮流量的影响较大,增大D1涡轮流量降低D2对涡轮流量的影响较小。Itis very important to assess the effect of the manufacturing tolerance of the trailing edge thickness on the turbine performance.To investigate the effect on the turbine performance,an one-stage-low-pressure turbine was analyzed by three dimensional calculation methods detailedly.Regarding to trailing edge thickness,there are two sets of calculations,A and B,with the trailing edge slot width c on stator and rotor geometry constant.In set A and B,the pressure side tip thicknessD1 and suction side tip thicknes D2 acted as variable respectively.The results indicates that：（1）the deviation of the tailing edge thickness always result in the decreasing of the turbine efficiency,compared with the efficiency of the turbine with designed trailing edge thickness.（2）the decreasing of D2 has little influence on the turbine performance.（3）the mass flux will decrease with the D1 increasing.The research results have an important referential meaning for understanding the effect of trailing edge thickness of the stator on the turbine perforraance.

关 键 词：尾缘厚度 涡轮性能 低压涡轮 尾缘劈缝 

分 类 号：TH16[机械工程—机械制造及自动化] TK14[动力工程及工程热物理—热能工程]