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针对涡轮叶顶密封性能的提高,对带圆形凹槽迷宫密封进行了构型优化研究。分析了不同压比时圆形凹槽数量、尺寸及分布对密封性能以及对涡轮做功效率的影响,初步探索了圆形凹槽降低损失的机理,给出了最佳的凹槽排列方案。结果表明,圆形凹槽的容积效应使泄漏流发生小角度偏转,降低了泄漏损失;压比增大,凹槽的节流能力减弱;所得凹槽最佳排列方案在压比为1.2时,泄漏系数降低了7.14%,效率提高了0.59%;单个凹槽半径由1mm增大到5mm,泄漏系数相对于光滑密封减小5.8%,效率增加0.35%。
In view of the improvement of sealing performance of turbine blade tip, the configuration optimization of circular groove labyrinth seal was studied. The effects of the number, size and distribution of circular grooves on the sealing performance and the work efficiency of the turbine at different pressure ratios were analyzed. The mechanism of reducing the loss of circular grooves was initially discussed and the optimal groove arrangement was given. The results show that the volume effect of the circular groove deflects the leakage flow at a small angle and reduces the leakage loss. When the pressure ratio is increased, the throttling capability of the groove is weakened. When the pressure ratio is 1.2, The leakage coefficient is reduced by 7.14% and the efficiency is improved by 0.59%. The radius of single groove is increased from 1mm to 5mm, the leakage coefficient is reduced by 5.8% compared with smooth seal, and the efficiency is increased by 0.35%.