跨声速轴流压气机流动损失分析  

Analysis of flow loss in transonic axial compressors

作　　者：杜文海[1] 吴虎[1] 孙娜[1] 

机构地区：[1]西北工业大学动力与能源学院,陕西西安710072

出　　处：《推进技术》2008年第3期339-343,共5页Journal of Propulsion Technology

基　　金：国家自然科学基金(10377013)

摘　　要：对跨声速多级轴流压气机的损失和落后角模型进行了改进,采用流线曲率法对非设计点进行了性能模拟。新的激波损失模型考虑了压气机工作状态从堵塞点向喘振点变化时激波系结构的变化;同时也考虑了压气机负荷对叶尖二次流动的影响。着重对跨声速轴流压气机在100%设计转速下各种损失的变化规律,以及叶片不同位置处的损失变化进行了分析,并得出了一些规律性的结论。计算得到的气动参数与实验值的比较表明:该模型能够较为准确地预测到跨声速压气机内部流动的叶型损失、激波损失、二次流损失以及展向掺混损失的变化规律。An improved streamline curvature numerical method is modified and applied to better approximate the flow fields of multi-stage transonic axial compressor, Improvements in the loss and deviation model include incorporation of a physics-based shock loss model which accounts for shock geometry changes from near-choke to near-stall, and loading effects on the tip secondary loss model. Specially, the characteristics of the loss components and the losses of different blade section are compared and analyzed under 100% design rotate speed, and some useful conclusions from those analyses are given. Data from a two-stage transonic axial compressor provides the basis for experimental comparisons, Overall comparisons demonstrate the improved loss and deviation model gives the general accurate results, indicating that the profile loss, the shock loss, the secondary and spanwise mixing loss relative to off-deslgn performance of the transonic axial compressor are adequately captured.

关 键 词：跨音速压气机 损失 数值仿真 

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]