超燃发动机燃烧室流场的数值模拟

推进技术 ›› 1996, Vol. 17 ›› Issue (1): 13-17.

超燃发动机燃烧室流场的数值模拟

梁剑寒,王承尧

国防科技大学航天技术系;国防科技大学航天技术系

发布日期:2021-08-15

NUMERICAL SIMULATIONS OF CHEMICALLY REACTING FLOWS IN SCRAMJET COMBUSTOR

Dept. of Astronautics, National Univ. of Defense Technology, Changsha, 410073;Dept. of Astronautics, National Univ. of Defense Technology, Changsha, 410073

Published:2021-08-15

摘要/Abstract

摘要： 用显式有限差分法对超燃发动机（Ｓｃｒａｍｊｅｔ）的燃烧室内流场进行了数值模拟。计算中采用了ＭａｃＣｏｒｍａｃｋ两步显格式、Ｂａｌｄｗｉｎ－Ｌｏｍａｘ代数湍流模型以及两方程、四组分的化学反应模型。为了解决源项的刚性问题，运用点隐式方法对它作了隐式处理。

关键词: 突扩燃烧室;超音速燃烧;流动分布;数值模拟

Abstract: Numerical simulations of chemically reacting flows in scramjet combustor have beencompleted, MacCortnack’s two step explicit scheme and Baldwin-Lomax algebric turbulence model areused. The chemistry model is a finite rate two equation model, A point-implicit method is used to treatthe source term.

Key words: ump combustion chamber;Supersonic combustion;Flow distribution;Numericalsimulation

梁剑寒,王承尧. 超燃发动机燃烧室流场的数值模拟[J]. 推进技术, 1996, 17(1): 13-17.