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。
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
出处
《推进技术》
EI
CAS
CSCD
北大核心
1999年第2期28-32,共5页
Journal of Propulsion Technology
基金
中国自然科学基金
航空科学基金
关键词
超燃
冲压发动机
燃烧室
超音速燃烧
数值仿真
Supersonic
combustion ramject engine,Ram air combustor,Supersonic combustion,Flow
distribution,Numerical simulation
