火箭发动机用合金GH202和GH586燃烧事故分析  

Combustion Failure Analysis of GH202 and GH586 Superalloys for Rocket Engine

作　　者：黄进峰[1] 赵光普[2] 焦兰英[2] 冯涤[2] 

机构地区：[1]北京科技大学新金属材料国家重点实验室,北京100083 [2]钢铁研究总院高温材料所,北京100081

出　　处：《钢铁研究学报》2005年第3期68-71,共4页Journal of Iron and Steel Research

摘　　要：对GH202、GH586合金部件在高温富氧工况下极短时间内就发生燃烧事故的原因进行了分析。结果表明:合金燃烧的主要原因是环境温度超过了合金的燃烧温度门槛值,而并非材料自身的问题;同时,对如何提高合金的抗燃烧性能及减少燃烧事故提出了建议和措施。Various parts made of GH202 and GH586 superalloy were ignited and combusted only in high pressure oxygen-enriched atmosphere for short time. The systematic experiments and analysis show that combustion event of above superalloys is due to the higher temperature which is in excess of ignition and combustion threshold temperature of GH202 and GH586 superalloy, rather than the quality of the alloy. In addition, some suggestions about increasing resistance to combustion, and decreasing combustion probabilities of alloys were proposed.

关 键 词：高温合金 燃烧 事故分析 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]