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本文中的实验在高压涡轮进口导叶平面叶栅中完成,叶栅端壁前缘开有模拟燃烧室涡轮连接处的缝隙。实验中采用GE-E~3高压涡轮进口导叶作为研究对象,缝隙与端壁表面夹角为30°。进口雷诺数(基于叶片轴向弦长和进口气流速度)为3.5×10~5,进口马赫数为0.1,泄漏流流量比为0.5%和2.0%。气膜有效度通过压力敏感漆(Pressure Sensitive Paint,PSP)进行测量。实验结果表明随泄漏流流量比的增加,端壁表面的平均气膜有效度有所增加;当来流攻角从i=+10°变化至i=-10°时,叶片前缘吸力面附近的端壁气膜有效度降低,但在整个端壁表面气膜有效度对攻角变化并不敏感。
The experiment in this paper is carried out in the high-pressure turbine inlet guide vane plane cascade. The leading edge of the end wall of the cascade opens the gap at the turbine connection of the simulated combustion chamber. In the experiment, GE-E ~ 3 high-pressure turbine guide vane was used as the research object, the angle between the gap and the end wall surface was 30 °. The inlet Reynolds number (based on the axial blade chord and inlet air velocity) is 3.5 × 10 -5, the inlet Mach number is 0.1, and the leakage flow ratio is 0.5% and 2.0%. The membrane effectiveness is measured by Pressure Sensitive Paint (PSP). The experimental results show that with the increase of the flow ratio of the leakage flow, the mean effective gas film thickness of the end wall surface increases. When the angle of attack of the flow changes from i = + 10 ° to i = -10 °, the suction near the blade leading edge The effectiveness of the end-wall gas film is reduced, but the effectiveness of the gas film on the entire end-wall surface is not sensitive to the change of the angle of attack.