Because of the flow separation of the corner region of compressor cascade,a little blade installed in leading edge of cascades was proposed to control the separation of corner region.After confirming the reliability of numerical simulation method with experimental data,numerical simulations were carried out to explore the effects of little blade on the performance of cascade.The results show that the aerodynamic performance at the attack angle range of-6° and 9° is improved by the use of little blade.It also decreases the total pressure loss,arises the static pressure ratio.Furthermore,little blade makes leading edge separation point of cascades corner move back,the area of the reverse flow is decreased and corner flow is improved.More fluid converges to middle of cascade,which improves the diffusion capacity of the cascade.%针对压气机叶栅角区流动易分离的特点,提出一种在叶栅前缘安装小叶片来抑制角区分离的新型流动控制方法.在利用叶栅试验数据确认数值模拟的可靠性后,对不同攻角下安装小叶片前后叶栅的流场特性进行了数值研究.结果表明:在-6°到9°攻角范围内小叶片改善了扩压叶栅的气动性能,使得总压损失减小,静压升增大.小叶片能使叶栅角区前缘分离点后移,角区分离线后的反流区面积减小,改善了角区流动;更多的流体汇聚到中间叶高,增强叶中部载荷,提高了叶栅的扩压能力.
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