气氢液氧同轴式单喷嘴燃烧室热态流场计算

推进技术 ›› 1996, Vol. 17 ›› Issue (4): 42-47.

气氢液氧同轴式单喷嘴燃烧室热态流场计算

王振国,周进,鄢小清,庄逢辰

国防科技大学航天技术系;国防科技大学航天技术系;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
基金资助:
国家自然科学基金

COMPUTATIONAL ANALYSIS OF FLOW IN LO₂/GH₂ THRUST CHAMBER WITH COAXIAL SINGLE INJECTOR

Dept. of Aerospace Technology, National Univ. of Defence Technology, Changsha, 410073;Dept. of Aerospace Technology, National Univ. of Defence Technology, Changsha, 410073;Dept. of Aerospace Technology, National Univ. of Defence Technology, Changsha, 410073;Dept. of Aerospace Technology, National Univ. of Defence Technology, Changsha, 410073

Published:2021-08-15

摘要/Abstract

摘要： 建立了欧拉－拉格朗日坐标系下液体火箭发动机内部工作过程二维轴对称两相湍流化学反应流的完全Ｎａｖｉｅｒ－Ｓｔｏｋｅｓ模型。应用该模型对气氢液氧同轴式单喷嘴燃烧室热态流场进行了数值模拟，得到了全流场的速度矢量分布、燃气组分等值线、流场等温线、流场等压线和流场等马赫线。计算是在任意斜交曲线坐标系下进行的，采用等参数正变换（代数变换）把物理平面上不规则计算域变换成了计算平面上的矩形域，控制方程也进行了相应的变换。计算结果表明，用计算流体力学（ＣＦＤ）的方法研究和分析液体火箭发动机内部工作过程是可行的。

关键词: 氢氧发动机;火箭发动机燃烧室;流动特性;数值模拟

Abstract: numerical model which emplpyes Eurlerian-Lagrangean Navier-Stokes equations todescribe the axisymmytric two phase turbulence reacting flow in liquid propellant rocket engine is presented in the paper. With this model, numerical simulation of the flow and combustion processes inLO2/GH2 thrust chamber with single coaxial injector was performed. The results obtained through thecomputation were showed in velocity vector plot and contour plots of gas species concentration, temperature, pressure and Mach number.Body-fitted coordinates were used in the numerical method to handle the irregular combustionchamber shape. Governing equations were transformed into the general form in non-orthogonal curvilinear coordinates (ξ, η), and discretized with SIMPLE algorithm. Numerical study shows that usingcomputational fluid dynamics (CFD) method to analysize the flow and combustion processes in liquidpropellant engine is practicable.

Key words: Hydrogen oxygen engine;Rocket combustion chamber;Flow characteristic;Numerical simulation

王振国,周进,鄢小清,庄逢辰. 气氢液氧同轴式单喷嘴燃烧室热态流场计算[J]. 推进技术, 1996, 17(4): 42-47.