摘要
Ｈ２／Ａｉｒ在两种不同的燃烧室尺寸、七种燃烧喷注方式下进行了系统的超声速燃烧实验。实验空气的滞止温度在２０００Ｋ左右，滞止压力１～１．４ＭＰａ，总流量２ｋｇ／ｓ，燃烧室进口马赫数２．５，可以模拟飞行Ｍ数为７的超燃冲压发动机中的燃烧工况。新开发的一维超声速燃烧程序ＳＳＣ－１可以估算出燃烧室内的流场参数、燃烧效率和总压损失。计算结果与实验进行了比较，发现较好的一致。实验结果表明，利用垂直喷射，燃烧效率可以超过８０％，同时不引起严重的总压损失。由燃烧室壁面静压分布与燃烧效率的分析发现，燃烧室燃料注射位置应避免过于集中，宜分散按规律分布，使燃烧室静压分布尽量平直以获得高燃烧效率。
Experimental and Analytical supersonic combustion studies were conducted in test combustors with integrated nozzle strut injectors under normal and combined normal and parallel injection.The tested air with a temperature of 2100k,pressure of 4.5 MPa and flow rate of 2.0kg/s was utilized for the experiment.The Mach number of the flow at the entrance of the test combustor is 2.5,thus the flight condition of Mach 7 of the scramjet can be simulated.In addition,an one dimensional supersonic combustion computer code SCC-1 in terms of wall static pressure data were developed for the estimation of flow field parameters,combustion efficiency and total pressure recovery.The calculated results were consistent with the experimental measurement.Experiment results showed that the combustion efficiency of 80% and above could be obtained by the normal injection.The factors affecting combustion efficiency and total pressure recovery were discussed.
出处
《流体力学实验与测量》
CSCD
1999年第1期1-12,共12页
Experiments and Measurements in Fluid Mechanics
基金
国家863航天技术专家委员会资助
国家自然科学基金
关键词
超声速燃烧
超燃
冲压发动机
燃烧效率
氢/空气
supersonic combustion
scramjet
mixing enhancement
combustion efficiency
total pressure recovery
