基于拟压缩方法的扩压器低速流场数值研究  

Numerical investigation of low-Mach number flowfield inside of vaned diffuser based on the pseudo compressibility method

作　　者：高丽敏[1] 雷蒋[2] 王欢[1] 

机构地区：[1]西北工业大学动力与能源学院翼型、叶栅空气动力学重点实验室,西安710072 [2]西安交通大学能源与动力工程学院,西安710049

出　　处：《航空动力学报》2009年第2期409-413,共5页Journal of Aerospace Power

基　　金：教育部博士点新教师基金(20070699034);西北工业大学高层次人才科研启动费以及"翱翔之星"计划

摘　　要：发展了基于拟压缩方法的求解叶轮机械低马赫数流场的方法,研制了时间推进方法对叶轮机械全流速范围流场的求解计算程序,且对拟压缩因子的取值进行了讨论.通过对离心压缩机叶片扩压器的数值计算表明,发展的基于拟压缩方法能够快速正确的预测叶轮机械内的低速流场;引入拟压缩方法是对时间推进方法的一个很好补充,使时间推进方法的应用范围得到了拓展.Owing to the type of the flow governing equation system, and the low efficiency of standard time--marching algorithm in solving the low Math number flows, a time marching code was explored to solve the incompressible internal flow field of turbomachinery based on the pseudo compressibility method. In the full paper, we explained our exploration in some detail; in this abstract, we just added some pertinent remarks listing three topics of explanation. In the first topic, a universal N-S equation system was derived, which can govern both high subsonic and low Mach number flow by a pseudo compressibility factor developed by Chorin. In the second topic, four step Runge-Kutta time-marching method with the central difference scheme was employed to resolve the N-S equations. Also in the second topic, we pointed out how the optimal pseudo compressibility factor was determined. In the last topic, some numerical results and the analysis for a vane diffuser of a tested centrifugal compressor were presented. The analysis of these results shows preliminarily that： （1） for the low Mach number flowfield, both efficiency and accuracy of the time marching algorithm based on the pseudo compressibility method is higher than that of the traditional time-marching algorithm; （2） the pseudo compressibility method is a compensator for the time-marching algorithm, and the application of the time-marching algorithm is extended by introducing the pseudo compressibility method.

关 键 词：拟压缩方法 时间推进法 叶片扩压器 低速流动 

分 类 号：V235.113[航空宇航科学与技术—航空宇航推进理论与工程]