跨声速轴流压气机特性计算用激波损失模型  

A shock loss model for the transonic axial compressor

作　　者：杜文海[1] 吴虎[1] 阮建刚[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》2007年第4期378-382,共5页Journal of Propulsion Technology

基　　金：国家自然科学基金(10377013)

摘　　要：基于实验结果,发展了一种适用于跨声速叶型的新激波损失模型,该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。将新激波损失模型应用于某两级跨声速轴流压气机特性预测中,计算与实验结果的比较表明,在跨声速轴流压气机非设计点性能预测中,该模型能够给出更为准确的结果,对于效率曲线的改进尤为明显,并且激波损失系数在全工况下的变化规律更加合理,这表明新激波损失模型能够准确地反映出跨声速压气机内部的流动机理和激波损失大小。A physics-based shock loss model combined with streamline curvature is presented and implemented to better approximate the flow fields of transonic axial compression systems. The shock loss model accounts for shock geometry changes from near-choke to near-staR. The importance of accounting for shock geometry and loss changes with operating conditions is clearly demonstrated. Data from a two-stage transonic axial compressor provides the basis for experimental comparisons. Overall and spanwise comparisons demonstrate that the shock loss model can improve performance prediction, especially for adiabatic efficiency prediction, indicating better understanding for the blade effects and the flow physics.

关 键 词：跨音速压气机 激波 损失 模型 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]