火箭喷管材料的热震试验及其分析

The Test and Analysis of Thermal Shock of Rocket Nozzle Materials

本文介绍了采用电炉加热、氧乙炔焰喷吹、等离子体喷吹以及发动机试车等四种试验方法对热解石墨、石墨渗硅、石墨沉积钨、钼、钼渗硅、Si_3N_4-SiC陶瓷及TiC基金属陶瓷等七种高温材料进行的热震性对比鉴定。试验表明,氧乙炔焰喷吹比较接近发动机试车的结果,它可作为筛选喷管材料的一种简易有效的方法。本文还提出了热震试验的技术规范以及热震等级的标准。讨论了影响材料热震性的各种因素以及改进喷管材料的主要技术途径。

This paper introduces the evaluations of the thermal shock resistance of seven high temperature materials (pyrolytic graphite, siliconized graphite, tungsten-deposited graphite, molybdenum, silicided molybdenum, ceramic Si_3N_4-SiC and cermat TiC-Mo-Ni), using the following methods: (1) furnace heating, (2) oxyacetylene flame heating, (3) plasma flame heating, (4) rocket engine test. Test results show that the oxyacetylene flame method is nearly as good as the rocket engine test. Thus the oxyacetylene flame test may be regarded as a simple and effective method for selecting rocket nozzle materials. Technical specification of such test and classification standard are proposed. Lastly, factors influencing the thermal shock resistance of materials and main technical approaches for improving nozzle materials are discussed.