超声速燃烧室流场的数值模拟研究

推进技术 ›› 1999, Vol. 20 ›› Issue (2): 28-32.

超声速燃烧室流场的数值模拟研究

刘敬华,凌文辉,马祥辉,刘陵,张榛,王新月

航天工业总公司３１所;航天工业总公司３１所;航天工业总公司３１所;西北工业大学航空动力与热力工程系;西北工业大学航空动力与热力工程系;西北工业大学航空动力与热力工程系

发布日期:2021-08-15
基金资助:
中国自然科学基金,航空科学基金

NUMERICAL SIMULATION STUDY OF SCRAMJET FLOW FIELD

Dept.of Aeroengine Engineering,Northwestern polytechnical Univ.,Xi′an,710072;Dept.of Aeroengine Engineering,Northwestern polytechnical Univ.,Xi′an,710072;Dept.of Aeroengine Engineering,Northwestern polytechnical Univ.,Xi′an,710072;Dept.of Aeroengine Engineering,Northwestern polytechnical Univ.,Xi′an,710072;Dept.of Aeroengine Engineering,Northwestern polytechnical Univ.,Xi′an,710072;Dept.of Aeroengine Engineering,Northwestern polytechnical Univ.,Xi′an,710072

Published:2021-08-15

摘要/Abstract

摘要： 用二维Ｎ－Ｓ方程的数值计算方法，模拟了超声速燃烧室内流场结构和性能。当量油气比φ＝０．３５和φ＝０．４６，燃烧室由扩张段和等截面段组成。在给定的进口状态下，计算结果与实验数据的比较表明，壁面压力和总压恢复系数相当符合。对计算的燃烧效率低于实验数据的原因进行了分析，对双模态超声燃烧室设计提出了改进的意见。

关键词: 超燃冲压发动机;冲压进气燃烧室;超音速燃烧;流动分布;数值仿真

Abstract: The construction and performance of air flow field in supersonic combustion were calculated by means of the solution for two dimensional N S equations.The combustor consisted of expansion and constant section.The equivalent fuel/air ratios were φ= 0 35 and φ =0 46 The results of given inlet condition show that wall pressures and total pressure recover coefficiency are in accordance with testdata.This paper also analyzes the reason why the combustion efficiencies of calculation are lower than the testdata,and makes a suggestion on modiffication design of dual mode combustor

Key words: Supersonic combustion ramject engine;Ram air combustor;Supersonic combustion;Flow distribution;Numerical simulation

刘敬华,凌文辉,马祥辉,刘陵,张榛,王新月. 超声速燃烧室流场的数值模拟研究[J]. 推进技术, 1999, 20(2): 28-32.