中文摘要：

这研究试验性地在 0 度的发生角度在汽轮机串联的流动领域上调查片尖端几何学的效果。测试在一条低速度的汽轮机串联风隧道被执行。雷纳兹数字在出口基于片弦是大约 172300。出口流动领域穿越被做以便测量全面表演。与一条弦明智的隧道使用扁平的尖端和投出的尖端的效果被学习。有扁平的尖端的案例作为基线被引用。尖端清理都是测量 0.84% 片跨度的 1 公里。隧道的深度是 2mm。在从落后于边的串联下游的 10% 弦的流动领域用微型在 38 个跨度明智的位置和 26 个沥青明智的位置被测量五洞的压力探查。尖端结束墙上的静态的压力分发在 16 个沥青明智的车站和 17 个弦明智的车站被测量。在那里存在的结果表演在为扁平的尖端和压力方面 squealer 尖端的压力方面的大压力坡度，它意味着强壮的漏流动。到吸方面的从压力方面的压力坡度极大地为投出的尖端被减少，并且产生的漏流动更弱。漏旋涡的核心为吸方面 squealer 尖端为压力方面 squealer 尖端并且远更近搬到吸方面离开吸方面。压力方面 squealer 几乎没在改进流动能力并且减少全面损失比扁平的尖端有小优点。吸方面 squealer 尖端和投出的尖端罐头有效地减少尖端漏旋涡的紧张，改进流动能力和经过和投出的尖端执行的汽轮机串联的还原剂损失最好。

英文摘要：

This study investigates the effects of blade tip geometry on the flow field of a turbine cascade at the incidence angle of 0 degree experimentally. The tests were performed in a low-speed turbine cascade wind tunnel. The Reynolds number based on the blade chord was about 172300 at the exit. Traverses of the exit flow field were made in order to measure the overall performance. The effects of using fiat tip and grooved tip with a chord-wise channel were studied. The case with the flat tip is referenced as the baseline. The tip clearances are all 1 mm measuring 0.84 percent of the blade span. The depth of channel is 2mm.The flow field at 10% chord downstream from the cascade trailing edge was measured at 38 span-wise positions and 26 pitch-wise positions using a mini five-hole pressure probe. The static pressure distribution on the tip end wall is measured at 16 pitch-wise stations and 17 chord-wise stations. Results show that there exists great pressure gradient in the pressure side for the fiat tip and the pressure side squealer tip, which means strong leakage flow. The pressure gradient from the pressure side to the suction side is greatly decreased for the grooved tip, and the resulting leakage flow is weaker. The core of the leakage vortex moves closer to the suction side for the pressure side squealer tip and farther away from the suction side for the suction side squealer tip. The pressure side squealer has little advantages over the fiat tip in improving the flow capacity and reducing the overall losses. The suction side squealer tip and grooved tip can effectively decrease the intensity of the tip leakage vortex, improve the flow capacity and reduce loss of the turbine cascade passage and the grooved tip performs the best.