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.
出处
《机械设计与制造》
北大核心
2013年第11期102-104,108,共4页
Machinery Design & Manufacture
关键词
尾缘厚度
涡轮性能
低压涡轮
尾缘劈缝
Trailing Edge Thickness
Turbine Performance
Low Pressure Turbine
Trailing Edge Slot
