超音平面叶栅激波损失模型的研究  

Research on the Shock Loss Model for Supersonic Cascades

作　　者：杨世豪[1,2] 赵庆军[1,3] 孙小磊[1] 徐建中[1] 

机构地区：[1]中国科学院工程热物理研究所,北京100190 [2]中国科学院大学,北京100190 [3]中国科学院轻型动力重点实验室,北京100190

出　　处：《工程热物理学报》2015年第2期292-296,共5页Journal of Engineering Thermophysics

基　　金：国家重点基础研究发展计划(973计划)(No.2010CB227302);国家自然科学基金(No.51206161)

摘　　要：对超音叶栅极限特征线以前流场特征的分析表明,外伸波系导致的总压损失主要受无量纲前缘半径(R_(le))和来流马赫数(Ma_(∞))影响。通过对理论解的简化,本文建立了计算外伸波系引起的总压损失的经验关系式。相比以前的损失模型,该关系式在0.0074<R_(le)<0.0148,1.1<Maa_(∞)<2.1时具有更高的精度。针对超音叶栅由未启动状态向启动状态转变的过渡状态,在分析前缘内伸波的激波形态时,本文认为采用内伸波波阵面和流道内流线始终垂直的处理方式更加符合内伸波波后亚音的流动特征,并依此建立了过渡状态下内伸波损失计算模型。通过和已有模型估算结果以及实验结果的对比可知,在过渡状态下,采用本文提出的内伸波损失模型,能够准确计算超音叶栅的前缘内伸激波损失。The study of flow field before the limiting characteristic show that losses caused by external shock system is mainly determined by the dimensionless leading edge radius(R_(le)) and inlet Mach number(Ma_(∞)).A related empirical equation is developed by simplifying the theory resolution.The empirical method is more accuracy than previous model in the range 0.0074< R_(le) <0.0148 and1.1 < Ma_(∞) <2.1.Besides,as the flow just behind the shock is subsonic at the transition condition from unstarted to started,it is more reasonable to assume that the passage shock on this occasion is perpendicular to the streamline everywhere.Based on this assumption,a model is established to calculate the passage shock loss.The comparison among predicted results of the present method,test data and calculated results of the previous model indicates that the passage shock loss model is able to predict the loss in the supersonic cascade accurately.

关 键 词：超音平面叶栅 外伸波 内伸波 激波损失模型 

分 类 号：O354.5[理学—流体力学]