【摘要】 本文对涡轮平面叶栅中叶尖间隙泄漏对涡轮叶栅流动的影响进行了实验研究。在出口马赫数分别为0.10,0.14和0.19时利用五孔探针在叶栅出口40%弦长处对总压损失系数进行了测量,并在每个出口马赫数下详细考虑叶尖间隙高度带来的影响,即1.0%H,1.5%H,2.0%H,2.5%H和3.0%H(H为叶片高度),最后对在展向上不均匀的叶尖间隙高度所带来的影响进行了研究。实验结果表明:在当前实验条件下,对于给定叶尖间隙高度,总体上出口马赫数对总压损失系数影响不大;当马赫数给定时,增大叶尖间隙高度,叶尖间隙泄漏流带来的总压损失几乎按比例地增加;增大相邻叶片叶尖间隙高度会增大中间叶片叶尖间隙泄漏损失;在当前实验条件下相对叶尖间隙高度变化带来的影响,相邻叶片叶尖间隙高度和出口马赫数的影响显得不重要。更多还原

【Abstract】 This article describes the effects of some factors on the tip clearance flow in axial linear turbine cascades. The measurements of the total pressure loss coefficient are made at the cascade outlets by using a five-hole probe at exit Mach numbers of 0.10,0.14 and 0.19. At each exit Mach number,experiments are performed at the tip clearance heights of 1.0%,1.5%,2.0%,2.5% and 3.0% of the blade height. The effects of the non-uniform tip clearance height of each blade in the pitchwise direction are also studied. The results show that at a given tip clearance height,generally,total pressure loss rises with exit Mach numbers proportionally. At a fixed exit Mach number,the total pressure loss augments nearly proportionally as the tip clearance height increases. The increased tip clearance heights in the tip regions of two adjacent blades are to be blame for the larger clearance loss of the center blade. Compared to the effects of the tip clear-ance height,the effects of the exit Mach number and the pitchwise variation of the tip clearance height on the cascade total pressure loss are so less significant to be omitted.更多还原