采用数值模拟方法对利用不同安装方式叶尖小翼控制压气机叶栅间隙流动进行研究。结果表明，不同安装方式叶尖小翼都可以有效降低叶顶泄漏流速，削弱泄漏涡强度。叶尖小翼改变了叶尖负荷及泄漏涡运行轨迹，进而影响了叶尖流场不同涡系之间的相互作用。吸力面小翼削弱了泄漏涡，抑制了通道涡的发展，使得叶栅总损失降低。压力面小翼及组合小翼削弱了泄漏涡，但增强了通道涡及其与泄漏涡之间的相互作用，叶栅总损失增加。
A numerical study has been conducted to explore the effects of three different blade tip winglet geometries on tip leakage flow field of compressor cascade. The current results show that a significant tip leakage velocity and strength of tip leakage vortex reduction is possible by using all three kinds winglet. The blade loading near the tip and the tip leakage vortex trajectories are changed by the tip winglets, thus the interaction between passage vortex and tip leakage vortex is also changed. The suction-side winglet can reduce the intensity of tip leakage vortex and suppress the development of passage vortex, thus the aerodynamic efficiency of the cascade is significantly improved. The pressure-side winglet and combined winglet can also reduce the intensity of tip leakage flow, but they strengthen the interaction between passage vortex and tip leakage vortex, thus the total loss of the cascade is increased.
参考文献
| [1] | Nicolas Gourdain;Francis Leboeuf .Unsteady Simulation of an Axial Compressor Stage With Casing and Blade Passive Treatments[J].Journal of Turbomachinery,2009(2) |
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