气动谐振管加热过程气体参数的测量与分析  

Measurement and Analysis of Gaseous Parameters for Gas-Dynamic Resonance Tube Heating Process

作　　者：安联[1] 梁国柱[1] 童晓艳[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100083

出　　处：《航空动力学报》2003年第3期415-419,共5页Journal of Aerospace Power

基　　金：国家自然科学基金(59906001)

摘　　要：实验研究了圆柱形、圆锥形和锥柱形三种结构形式的气动谐振加热管,采用高温高频压力传感器和灵敏度较高的温度传感器直接测量了谐振管加热过程中谐振腔底气体的压力和温度的时间历程。实验结果确认了谐振管加热的主要机理是激波振荡累积加热机制,而且表明谐振温升与管内气体压力振荡幅值有关,而谐振管压力振荡幅值与驱动气体压力有关;结构形式不同的谐振管,加热特性显著不同。实验结果有助于液体火箭发动机谐振管点火器的实际设计,而且可以用来检验数值模拟的正确性。The experimental measurements of gaseous pressure and temperature histories at the end of the resonance cavities of three types of resonance tubes, i. e. , cylindrical, cone and cone-cylinder shaped tubes were carried out by employing high frequency heat - resistant pressure transducers and thermocouples. The experimental results confirm that the intense oscillating shock wave accumulating dissipation is surely the major heating mechanism of the resonance tube. The gas in the tube is irreversibly compressed to a high time-averaged temperature over the stagnation temperature of the jet. The results also show that resonance tube heating effects are related to the pressure oscillations in the tubes,whereas the pressure oscillations are related to the pressure of the driving gas,and further,different types of resonance tubes have significantly different heating properties. The results are useful for actual designing of resonance tube igniters of liquid rocket engines and can be used as typical data for verifying correctness of numerical simulation.

关 键 词：气动谐振管 驱动气体压力 实验 激波加热 液体火箭发动机 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]