摘要
采用一维无粘理论对扩张喷管的流动和性能进行了计算,研究了壁面散热量和散热规律对喷管流动、出口气流参数和性能参数的影响。结果表明:壁面散热会导致喷管沿程静压、静温和总温减小、出口马赫数和总压增大,并且随散热量增大,喷管的工作状态可依次经历欠膨胀状态、临界状态和过膨胀状态,但是喷管的推力系数逐渐减小,性能下降;壁面散热规律对喷管性能有很大影响,入口附近散热量较大出口附近散热量较小时,喷管的性能下降最大。从研究结果可以看出,壁面散热可以调节喷管的欠膨胀度,使喷管从欠膨胀状态趋于过膨胀状态,采用侧重于后半部分散热的规律可以取得良好的调节效果。
One dimensional non-viscous theory is used to calculate the flow characteristics and performance of a divergent nozzle, and analyze the effect of wall surface heat dissipation and heat dissipation law on flowfield, exit dynamic parameters and performance parameters of the nozzle. The calculated results show that the wall surface heat dissipation may cause decrease of static＇ pressure, static temperature and total temperature, but increase of exit Mach number and total pressure, and descend of the nozzle performance, and may result in, with gradual addition of heat dissipation, the nozzle will suffer from under-expansion and over-expansion, but its thrust coefficient becomes gradually decreased. Besides, the law of heat dissipation will have great influence on nozzle performance. The research result indicates when heat dissipating capacity is higher near inlet and lower near outlet of the nozzle, the nozzle performance decreases most. It is found from these results that the heat dissipation on wall surface of the nozzle can regulate the operation condition of nozzle,from under expansion to critical expansion. The heat dissipation from rear part of the nozzle can achieve a perfect adjusting effect.
出处
《火箭推进》
CAS
2015年第3期33-38,共6页
Journal of Rocket Propulsion
基金
国家863项目(2012AA702308)
关键词
喷管
散热规律
推力系数
理论分析
nozzle
heat dissipation law
thrust coefficient
theory analysis
