单级跨音速压气机内流场的非定常模拟及损失分析  

Unsteady loss analyses of the flow in single-stage transonic compressor

作　　者：孙宇涛[1] 任玉新[1] 

机构地区：[1]清华大学工程力学系,北京100084

出　　处：《清华大学学报（自然科学版）》2009年第5期759-762,共4页Journal of Tsinghua University(Science and Technology)

基　　金：国家自然科学基金资助项目(10572075);GEAE大学策略联盟计划项目

摘　　要：通过数值求解非定常三维可压缩Reynolds平均Navier-Stokes(RANS)方程,模拟了跨音速压气机级Rotor35/Stator37内的流场。为了分析该压气机级的损失,推导了描述非定常流动损失的参数(不可逆性)及其对应的强度量参数。以此为基础,研究了损失和流动结构之间的关系,得到了不同流动结构在损失产生上的主次关系;并定量给出了主要区域损失的大小。发现在最高效率点附近,边界层产生最大的损失,然后是顶隙泄漏流动、尾迹,以及核心区流动。该文也对该级压气机进行了损失功分析,结果表明吸力面边界层以及顶隙泄漏流动对于损失产生贡献最大。The losses in a transonic compressor stage operating at peak efficiency were studied numerically by solving the 3D unsteady RANS equations. The losses are studied based on the thermodynamic irreversibility and its intensive equivalent called the intensity of irreversibility which account for the unsteady effects. The relative importance of the various flow structures on the losses are identified based on the intensity of irreversibility. An audit of the irreversibility shows that the boundary layers produce the largest losses followed by the tip leakages, wakes and core flow. An audit of the irreversibility shows the importance of the suction surface boundary layers and the tip leakages on the loss generation.

关 键 词：跨音速压气机 动静叶干涉 损失分析 

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] V231.1