新型纽扣式涡喷发动机压气机数值模拟  

Numerical Simulation on Compressor of A New Button Turbojet Engine

作　　者：马红鹏[1] 方蜀州[1] 高凤川[2] 高航[1] 李腾[1] 方冠林 

机构地区：[1]北京理工大学宇航学院,北京100081 [2]西安航天动力研究所,西安710100

出　　处：《弹箭与制导学报》2016年第5期71-76,80,共7页Journal of Projectiles,Rockets,Missiles and Guidance

基　　金："十一五"民用航天科研预先研究项目(2220062202)资助

摘　　要：压气机作为涡喷发动机的核心,其内流场特性是研究的重点。文中基于国内外微小型涡喷发动机研究,设计了一种纽扣式涡喷发动机,利用SOLIDWORKS建立三维模型,并对此压气机进行三维粘性流场数值计算,得到了压气机怠速、额定和极限3个工作状态的各方面特性曲线,分析并总结了压气机的设计要素。计算结果与国内外其他研究数据进行对比,结果表明,压气机性能良好,满足设计要求,该设计经验为超微小型涡喷发动机提供参考依据。Compressor is the core of micro turbojet engine, internal flows and characteristics are keys of the research. Based on micro small turbojet engine research both at home and abroad, this paper elaborates a button turbojet engine, the SOLIDWORKS was adopted for 3d model, compressor＇ s three-dimensional viscous flow field was simulated, the characteristic curves of compressor＇ s idle, rated and limit working states were got, the compressor＇ s design elements were analyzed and summed up. Compared with other research data at home and abroad, the results show that the compressor performance is good, meets the design requirements. The design experience provides a reference basis for ultra-small turboiet engine.

关 键 词：纽扣式涡喷发动机 超微小型压气机 设计要素 数值模拟 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]