低压涡轮导向器气动性能的实验研究

Experimental Investigation of Aerodynamic Characteristics of LP Turbine Guide Vane

为了考查低压涡轮导向器的气动性能,在低速环形叶栅风洞上对导向器的实验叶栅进行了吹风实验。测量了由栅前至栅后共6个横截面的气动参数分布以及叶片和上、下端壁表面的静压场。实验结果表明,主流区的损失并不太大,主要的损失发生在上、下端壁附近,尤其是上端壁附近的损失非常大。引起叶栅损失的主要根源在于叶栅子午面较大的扩张,进一步降低叶栅的损失应从改进叶栅通道的子午面型线出发。

For validating the aerodynamic characteristics of LP turbine guide vane, the wind blow was carried out for test cascade of the guide vane on the low speed annular wind tunnel. The aerodynamic parameters distribution at six transverse sections from inlet to outlet of the tested cascades and the static pressure fields on the blade and the endwalls surfaces are measured. The test result shows that the loss in the mainstream is not large, most losses occur near two endwalls, especially the shroud. And the main source of the loss is the large divergence of the meridian plane. It will improve the profile of meridian plane of the cascade passage through more reducing the loss of the cascade.