尾缘厚度对涡轮叶栅性能影响的数值研究  

Numerical investigation on the effects of trailing edge thickness on turbine blade cascade performance

作　　者：郭湘锟 白涛[3] 张少博[1,2] GUO Xiang-kun;BAI Tao;ZHANG Shao-bo(National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics,School of Energy and Power Engineering,Beijing University of Aeronautics and Astronautics,Beijing 100191,China;Collaborative Innovation Center for Advanced Aero-Engine,Beijing 100191,China;School of Aircraft,Xi’an Aeronautical University,Xi’an 710077,China)

机构地区：[1]北京航空航天大学能源与动力工程学院航空发动机气动热力国家重点实验室,北京100191 [2]先进航空发动机协同创新中心,北京100191 [3]西安航空学院飞行器学院,西安710077

出　　处：《燃气涡轮试验与研究》2016年第5期11-16,共6页Gas Turbine Experiment and Research

摘　　要：采用数值模拟方法,分别通过改变亚声速和超声速叶型尾缘厚度,研究尾缘厚度变化对涡轮叶栅损失的影响,并在宽广工况范围内探讨尾缘厚度对涡轮叶栅性能影响的敏感性。结果表明:尾缘厚度对亚声速叶型的影响较小,涡轮叶栅损失随尾缘厚度的增大而增大;尾缘厚度对超声速叶型的影响较为明显,随着尾缘厚度的增大,尾缘附近的激波强度增强,叶栅通道中的损失明显增大。对于本文所研究的超声速叶型,尾缘厚度的影响在非设计攻角下不会被放大;但随着马赫数的变化,尾缘厚度的影响规律不同。Using numerical simulation method, the effects of trailing edge thickness on turbine blade cascade loss was investigated by changing trailing edge thickness of the subsonic blades and supersonic blades respectively, and the problem of the influence sensitivity of trailing edge geometric parameters on turbine cascade performance was discussed in broad working conditions. The results show that the thickness of trailing edge has little effect on the subsonic blades, turbine cascade loss increases with the increase of the thickness of the trailing edge; the influence on the supersonic blade is relatively obvious, the strength of shock wave near trailing edge increases with the increase of the thickness of trailing edge and the loss in the cascade increases. For the supersonic blades, the influence from trailing edge thickness won’t be heightened under off-design attack angle; but as Mach number varies, the influence rule of trailing edge thickness will be different.

关 键 词：航空发动机 涡轮 尾缘厚度 叶栅损失 尾迹 激波 数值模拟 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]