摘要
介绍了氢氧直流同轴式喷嘴结构参数对流量特性的影响的热试验研究结果,并采用一维数值分析模型计算了结构参数对喷嘴流量特性的影响。结果表明:计算结果与热试数据相吻合。喷嘴结构参数变化将引起喷嘴压力损失变化,并导致喷嘴流量特性发生变化;氢氧喷嘴流量系数随缩进深度增大而减小;氢喷嘴流量系数随环形间隙增大而减小,氧喷嘴流量系数则反之。
Effects of design parameters on hydrogen-oxygen coaxial injector discharge coefficient were investigated by hot tests and numerical analysis. Experimental and theoretical analysis results are in good agreement. The deeper recess length of liquid post leads to smaller injector discharge coefficients of oxygen and hydrogen. The larger annular gap leads to a greater oxygen discharge coefficient but a smaller hydrogen discharge coefficient.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2005年第4期689-692,共4页
Journal of Aerospace Power
关键词
航空
航天推进系统
喷嘴
流量特性
氢氧
aerospace propulsion system
injector
discharge coefficient
hydrogen-oxygen
