高速涡轮发动机技术发展浅析  

High Speed Turbine Engine Technology Development

作　　者：杨天宇[1] 张彦军[1] 芮长胜[1] 

机构地区：[1]中航工业沈阳发动机设计研究所,辽宁沈阳110015

出　　处：《燃气涡轮试验与研究》2013年第6期26-30,共5页Gas Turbine Experiment and Research

基　　金：航空科学基金(2012ZB06002)

摘　　要：根据高速飞行器的发展趋势,介绍了高速涡轮发动机概念及应用背景。通过分析国外典型高速涡轮发动机产品及研制计划,归纳出高速涡轮发动机的基本特征:以现有涡轮发动机为基础,采用组合循环、进气预冷等扩包线技术,具有耐高温能力。鉴于此,提出高速涡轮发动机的发展,需突破进气预冷、先进加力/冲压燃烧室设计、冷却与热防护、先进进排气系统设计等关键技术。同时,对高速涡轮发动机的技术发展也提出了初步设想。Advanced high speed turbine engine concept and the application background were introduced based on the development trend of high speed vehicle. Typical high speed turbine engines and research projects were analyzed to conclude essential characteristics of advanced high speed turbine engine. Based on traditional turbine engine, the high speed engine adopts combined cycle, mass injection pre-compressor cooling （MIPCC） and other technologies to extend envelope, and be high-temperature resistant. In view of the essential characteristics mentioned above, it is believed that MIPCC technology, advanced afterburner/ramjet burner design, cooling and thermal protection, advanced inlet and exhaust design and other key tech-nologies should be applied to break the bottleneck of high speed turbine engine development. At the same time, the preliminary visualization of high speed turbine engine development was proposed.

关 键 词：高超声速 高速涡轮发动机 扩包线技术 组合循环 进气预冷 热防护 

分 类 号：V235[航空宇航科学与技术—航空宇航推进理论与工程]