大流量火箭蒸汽发生器试验研究

Experimental Investigation on Rocket Steam Generator with High Flowrate

关键词:  火箭蒸汽发生器  燃烧  高空模拟 

Key words:  Rocket steam generator  Combustion  Altitude simulation

摘要:

为满足大流量高能引射工质发生装置研制的需要,在地面试验台上,对自行研制的大流量液氧酒精火箭蒸汽发生器进行了试验研究。试验结果表明,蒸汽发生器起动建压时间约2.0秒,主级段各性能参数平稳,蒸汽流量约40kg/s,蒸汽压力约0.86MPa,蒸汽温度约254℃,水蒸汽体积浓度80%。喷注器面板的氧化膜能够有效地阻止高温燃气向喷注面内部的扩散,延长喷注面寿命。大流量火箭蒸汽发生器可作为大型主动引射高空模拟试验台的蒸汽源。 

Abstract:

In order to meet the demand of large flow rate steam supply, the rocket steam generator, using of liquid oxygen and alcohol, was developed and tested on the ground bench. The test results show that, the pressure build up time in combustion chamber is about two seconds, and typical steam parameters, such as pressure , flow rate, temperature and water vapor volume concentration, were 0.86MPa, 40kg/s, 254℃, 80%, respectively. When total tested time exceeds thousand seconds, oxidation film formed on the injector panel can effectively prevent the spread of hot gas to the internal, and enhance the life duration of injector. As large flow steam source, the rocket steam generator may be applicable for altitude simulation facility. 