单级跨声风扇处理机匣径向倾角变化对性能的影响  

Impact of Different Radial Obliquity of Casing Treatment on Single Stage Transonic Fan Performance

作　　者：黄磊[1] 余华蔚[1] 吴艳辉[2] 

机构地区：[1]中国燃气涡轮研究院,四川成都610500 [2]西北工业大学动力与能源学院,陕西西安710072

出　　处：《燃气涡轮试验与研究》2011年第4期20-24,共5页Gas Turbine Experiment and Research

摘　　要：采用全三维定常数值方法研究轴向倾斜缝径向倾角变化对某单级跨声风扇性能及内部流场的影响,在该风扇上进行了两种常用不同倾角的数值研究。数值结果表明,两种不同倾角的机匣处理都提高了风扇的失速裕度,但也使得风扇的等熵效率减小。在相同机匣结构下,45°倾角比60°倾角的扩稳效果更好,效率损失也更小。另外,还详细分析了风扇内部流场,揭示了倾角变化对风扇性能影响的流动机理。The impact on performance and inner flow filed of the variety of radial obliquity of axial skewed slots for a single stage transonic fan was investigated with 3D steady numerical method. Two kinds of common different obliquity were researched in the fan. The numerical results showed that two kinds of different obliquity casing treatment not only increased the fan stall margin but also decreased the fan isentropic efficiency appreciably. For the same casing structure, the obliquity of 45 degree was prior to the obliquity of 60 degree in increasing stable operation range and efficiency. The fundamental flow mechanism was obtained by analyzing the fan flow field, which reveals the effects of different obliquity on fan performance.

关 键 词：单级跨声风扇 机匣处理 径向倾角 流场 机理 

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]