组合抽吸对跨音速压气机稳定性影响分析  

Analysis on Effects of Combined Boundary Layer Suction for Transonic Compressor Stability

作　　者：王掩刚[1] 任思源[1] 国睿[1] 赵龙波[1] 

机构地区：[1]西北工业大学 动力与能源学院,西安710072

出　　处：《航空工程进展》2012年第3期351-356,共6页Advances in Aeronautical Science and Engineering

基　　金：国家自然科学基金(50806061);西北工业大学翱翔之星计划

摘　　要：为研究组合抽吸对跨音速压气机稳定性的作用,以NASA Rotor35为研究对象,应用数值模拟手段深入分析了不同抽吸方案对该压气机稳定性以及流场结构的影响效应,数值计算采用商业软件NUMECA结合S-A模型,求解定常N-S方程组。研究结果表明:叶表和端壁组合抽吸不仅对压气机的压比和效率性能有较大的提升,同时对压气机内部的流动失稳机制有抑制作用,是一种可行的流动失稳控制策略;叶表抽吸缝主要是吸除叶片吸力面附面层内的低能高熵流体提高压气机的效率,端壁抽吸主要是吸除叶顶内低能高熵流体,改善叶顶复杂流动结构,进而扩大压气机稳定工作范围。The effect of combined boundary layer suction（BLS） on the stability and flow structure of NASA Ro- tor35 has been investigated by numerical simulation with different schemes of suction, the NUMECA software with S-A model is used to solve the constant N-S equation group. The results show that： combination suction of blade surface and end-wall can not only improve the compressor＇s pressure ratio and efficiency highly, but also can restrain the inside instable flow of the compressor, which is a highly feasible control strategy for the corn pressor instability; blade surface suction improve the compressor＇s efficiency by mainly aspirating the lower en- ergy airflow of the blade suction surface layer, and end-wall suction mainly aspirates the lower energy airflow to improve the flow structure near the rotor tip, which could lead to improve the stall margin of the compressor.

关 键 词：跨音速压气机 附面层抽吸 抽吸位置 流动稳定性 组合抽吸 

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]