弹用微小型涡轮发动机的发展及关键技术分析  

Development and Key Techniques Analysis of Microturbo Engine for Missile

作　　者：史朝龙[1] 

机构地区：[1]海军驻航天三院军事代表室,北京100074

出　　处：《战术导弹技术》2015年第4期46-52,共7页Tactical Missile Technology

摘　　要：为探索微小型涡轮发动机发展途径,对国际上20~550kgf推力级范围内的先进导弹动力系统进行了综述。结合导弹总体的发展应用需求,对适用于弹用微小型涡轮发动机未来发展的关键技术进行了分析。通过分析可以看出,为实现弹用微小型涡轮发动机宽推力型谱、高推重比、低油耗、低成本的技术指标,着重发展高效压缩系统技术、先进燃烧组织技术、特种材料技术、低成本设计制造技术等关键技术势在必行。To find the develped-method of micro-turbine for missiles, the micro-turbines for advanced missiles which＇ s thrust range from 20kgf to 550kgf on internation is summarized. Combining the missises＇ technique-demand, kinds of techniques which are very important to the advanced micro-turbine are intro- duced. Firstly, the result show that the futural mirco-turbine will be broad thrust, low cost, and the rate of oil-consumption of micro-turbine will drop off, the thrust-weight ratio of micro-turbine will increase. Secondly, four key-techniques would very important to the developing of advanced micro-turbine, inclu- ding high efficiency air compression technology, advanced combustion technology, advanced material technology, low-cost design and manufacturing technology.

关 键 词：导弹 微小型涡轮发动机 关键技术 

分 类 号：V235.11[航空宇航科学与技术—航空宇航推进理论与工程]