预燃室三维湍流和燃烧过程的数值模拟(Ⅱ)数值模拟结果及分析

推进技术 ›› 2002, Vol. 23 ›› Issue (3): 193-197.

预燃室三维湍流和燃烧过程的数值模拟(Ⅱ)数值模拟结果及分析

冯喜平,何洪庆,葛李虎

西北工业大学航天工程学院;陕西西安710072;西北工业大学航天工程学院;陕西西安710072;陕西动力机械设计研究所;陕西西安710100

发布日期:2021-08-15
基金资助:
国家“八六三”基金资助项目 (86 3 2 3 3 2 )

Numerical simulation on 3-D turbulent flow and combustion process (Ⅱ) Results and analysis

Coll of Astronautics, Northwestern Polytechnical Univ , Xi’an 710072,China;Coll of Astronautics, Northwestern Polytechnical Univ , Xi’an 710072,China;Shaanxi Engine Design Inst , Xi’an 710100,China

Published:2021-08-15

摘要/Abstract

摘要： 用三维湍流N S方程和单步快速不可逆化学反应描述液氧煤油液体火箭发动机预燃室内的三维湍流和燃烧过程。采用同位网格和SIMPLE算法求解控制方程 ,得到了喷注单元和预燃室内参数的详细分布。结果表明 ,预燃室结构设计合理 ,其出口处燃气浓度、温度分布均匀 ,质量加权平均温度与实际温度接近。同时表明 ,预燃室头部的喷注单元和液氧二次喷注孔的结构排列 ,喷注单元的流动和燃烧状况 ,液氧二次喷注孔的入口参数等 ,对预燃室出口燃气温度等参数分布的均匀性影响很大

关键词: 液体推进剂火箭发动机;预燃室;三维流;湍流燃烧;反应流;数值仿真

Abstract: Three dimensional Navier Stokes equations and one step fast non reversible chemical reactions were employed to describe the flow and the combustion of the pre burner of an oxygen /kerosene liquid rocket engine The equations were solved using SIMPLE method in the co located grids, then the detail distribution of gas parameters was obtained The results show that the structure is suitable and the temperature distribution in the outlet section of the pre burner is uniform and the mass weighted average temperature in this section is closed to the practical mass weighted average temperature The results also show arrangement of injectors on head of pre burner and second liquid oxygen injecting holes, flow and combustion of injectors and entrance parameters of second liquid oxygen injecting holes exert a tremendous influence on well distribution of gas temperature and other parameters

Key words: Liquid propellant rocket engine;Precombustion chamber;Three dimensional flow;Turbulent combustion;Reacting flow;Numerical simulation

冯喜平,何洪庆,葛李虎. 预燃室三维湍流和燃烧过程的数值模拟(Ⅱ)数值模拟结果及分析[J]. 推进技术, 2002, 23(3): 193-197.