轴流压气机转子尖部三维复杂流动Ⅱ——数值模拟研究  

Three-dimensional Flows near Rotor Tip in an Axial Compressor Ⅱ——Numerical Simulation Study

作　　者：于贤君[1] 刘宝杰[1] 蒋浩康[1] 

机构地区：[1]北京航空航天大学航空发动机热动力国防重点实验室,北京100191

出　　处：《航空学报》2010年第1期58-69,共12页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金(50476001);国家重点基础研究发展计划课题(2007CB210103);北京航空航天大学博士研究生创新基金

摘　　要：在实验研究和理论分析的基础上,对亚声速压气机转子尖部复杂流动做了数值模拟研究,旨在进一步深入研究叶尖间隙和进口总压分布对转子叶尖复杂流动的影响。首先通过对与实验条件相同的转子尖部复杂流动的数值模拟研究,校验了数值模拟结果,并分析了转子尖部复杂流动速度场、压力场和涡量场分布特性。然后通过改变叶尖间隙尺度和进口总压分布,研究了二者对近叶尖复杂流动的影响。研究结果表明:当叶尖间隙小于1%叶片弦长时角区旋涡的发展是导致转子失速的关键;而当叶尖间隙大于2%叶片弦长时叶尖泄漏涡的发展是导致转子失速的关键;改变进口总压分布可以合理地组织转子尖部流动并扩大转子工作裕度。此外,通过观测近叶片吸力面二维涡线的发展趋势可以判断叶尖复杂流动的发展状态。Based on experimental and theoretical studies of the three-dimensional rotor tip flows in a low-speed axial compressor,numerical simulation studies are conducted to clarify the effects of the changing tip clearance sizes and total inlet pressure distributions on the rotor tip flows. First,numerical simulation is conducted with the same geometry and boundary conditions as those in the experimental investigation,and the simulated results are validated by the experimental results. Further studies of the near tip flows are conducted by analyzing the simulated velocity,vorticity and static pressure fields. Then,by changing the tip clearance sizes and total inlet pressure distributions,numerical simulation is performed again and the near tip flows are analyzed in detail. The results show that when the tip clearance is smaller than 1% of the blade chord,the evolution of the corner vortex determines the stability of the rotor; however,as the tip clearance increases to 2% of the blade chord,the tip leakage vortex becomes the key flow structure. Moreover,it is found that the evolution procedure of the near suction surface two-dimensional vortex lines has a close relationship with the rotor tip flows.

关 键 词：叶尖泄漏涡 角区旋涡 二次流 数值模拟 压气机 

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]