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论文以实际应用中出现破裂的向心涡轮为研究对象,研究导流叶片尾缘激波、导流叶片叶尖间隙泄漏流动以及导流叶片尾迹对转子叶片表面压力波动的干涉作用,定性确定这三种因素在转子叶片表面压力波动中所占比重大小,发现激波和导流叶片叶尖间隙泄漏流动所诱导的转子叶片压力波动位置。结果表明,激波和导流叶片叶尖间隙泄漏流动是导致转子叶片表面压力波动的主要因素;受向心涡轮叶轮进口形状的影响,激波只是和转子叶片前缘附近的吸力面发生作用,导流叶片开度减小,激波强度增大,转子叶片压力波动幅值明显增大;导流叶片叶尖和叶根间隙泄漏流动会导致转子叶片吸力面叶尖和叶根的压力波动明显增大,是转子叶片前缘叶尖发生高周疲劳的主要原因.
In this paper, the radial turbine with rupture in practical application is taken as the research object to study the interference effect of the shock wave at the trailing edge of the guide vane, the tip clearance of the guide vane and the wake fluctuation of the guide vane on the pressure fluctuation of the rotor blade surface. Three kinds of factors in the rotor blade surface pressure fluctuations in the proportion of the size of the shock wave and guide vane tip leakage flow induced rotor blade pressure fluctuations position. The results show that the leakage of shock tip and guide vane tip clearance is the main factor leading to the pressure fluctuation on the rotor blade surface. The shock wave only affects the suction surface near the leading edge of the rotor blade due to the shape of the inlet of the turbine impeller. The opening of the guide vane is reduced and the shock strength is increased and the pressure fluctuation amplitude of the rotor vane is obviously increased. The leakage flow at the tip and the root of the guide vane can cause the pressure fluctuation at the blade tip and the root of the rotor blade to fluctuate significantly Increase, is the main reason for the high cycle fatigue of the blade tip leading edge.