基于新型非结构有限体积解耦算法的激波诱导燃烧数值模拟  

Numerical Simulation of Shock-induced Combustion with a New Uncoupled Algorithm in Unstructured Finite Volume Method

作　　者：刘瑜[1] 刘君[1] 白晓征 

机构地区：[1]国防科技大学航天与材料工程学院,湖南长沙410073 [2]总参陆航研究所,北京101121

出　　处：《国防科技大学学报》2011年第6期139-144,共6页Journal of National University of Defense Technology

基　　金：国家部委基金资助项目

摘　　要：把基于结构网格有限差分方法建立的化学非平衡流动模拟的新型解耦算法推广到基于非结构网格的有限体积法,从而可用于模拟复杂几何构型下的化学反应流动。对H2/Air预混气体中激波诱导振荡燃烧的Lehr实验进行了数值模拟,计算得到的振荡频率与实验结果符合很好,表明计算方法具有时间和空间二阶精度。通过对不同几何外形发射体的计算发现,在其他条件相同的前提下,发射体的几何外形对激波诱导振荡燃烧的模式起决定作用。切削角小于等于15°时为规则模式下的高频振荡燃烧,切削角大于等于20°时为大扰动模式下的低频振荡燃烧。A new uncoupled algorithm of simulating chemical non-equilibrium flow originally realized by finite difference method was extended to the unstructured finite volume method,which makes the simulation of reaction flow in complex configurations possible.The H2/Air shock-induced oscillating combustion experiment conducted by Lehr was simulated,and the computed oscillating frequencies conformed well with the ones acquired by experiment,which indicates that the present method is temporally and spatially second order accurate.It is also demonstrated that geometrical configuration plays a definitive role in the combustion regime.If the truncated angle is less or equal to 15 degrees,high frequency oscillating combustion in regular regime occurs,while if the angle is larger or equal to 20 degrees,low frequency oscillating combustion in large-disturbance regime is observed.

关 键 词：激波诱导燃烧 解耦算法 计算流体力学 非结构网格 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]