Abstract: In order to reduce the turbine blade tip clearance leakage，application of the method about numerical simulation and experiment to research the tip clearance leakage flow formation mechanism，turbine adaptive tip jet hole control mechanism and its control of flow gap was carried out. On this basis，focuses on the adaptive tip jet hole parameters about the import position，the outlet position，jet hole diameter and the size of blade tip clearance，on the tip of the jet effect. The results showed that adaptive tip jet hole import position leaves little effect on the performance of the tip jet when the export position located in the middle of the tip and close to the pressure surface，the tip jet can get the best performance with the adaptive tip jet hole diameter being 2mm (d/H=4.8% relative blade height)，the adaptive tip jet hole can get better performance. The larger the tip clearance，the worse the effect of jet tip. When the tip clearance gets to 2mm (t/H=4.8% relative blade height)，the adaptive tip jet hole have lost the effect of blocking flow.

Key words: Adaptive；Tip jet hole；Clearance leakage flow；Jet hole parameter

摘要： 为了达到减小涡轮叶片叶顶间隙泄露的目的，应用数值模拟并辅之试验的方法对叶顶间隙泄漏流动形成机理、涡轮自适应叶顶喷气控制机理及其对间隙流动的控制作用进行了研究。在此基础上，着重研究了进口位置、出口位置、喷气孔直径等自适应叶顶喷气孔参数以及叶顶间隙大小，对叶顶喷气效果的影响规律。结果表明:自适应叶顶喷气孔进口位置对叶顶喷气性能影响不大；出口位置在叶顶中部，靠近压力面时，叶顶喷气效果最佳；喷气孔直径为2mm (d/H=4.8%相对叶高)时效果较好；叶顶间隙越大，叶顶喷气效果越差，当间隙取到2mm (t/H=4.8%相对叶高)时，叶顶喷气已经失去控制间隙泄漏的作用了。

关键词: 自适应；叶顶喷气孔；间隙泄漏；喷气孔参数