微型涡轮喷气发动机发展综述  

An Overview on Development of Micro Turbojet Engines

作　　者：薛然然[1] 李凤超[1] 

机构地区：[1]中国航空工业集团公司中国航空研究院,北京100012

出　　处：《航空工程进展》2016年第4期387-396,共10页Advances in Aeronautical Science and Engineering

摘　　要：100daN以下推力的微型涡轮喷气发动机能为微小型飞行器提供优质和可靠的动力,已成为国内外研究的热点。微型涡轮喷气发动机具有尺寸小、转速高、零件数少、工作时间长、推力易调节、红外辐射低、能重复使用等优点。其推重比已经超过11.0,已在无人作战飞行器、防空武器靶标、精确打击弹药、试验飞行器等装备上大量应用。本文从研发机构与代表产品、性能与结构特点、应用现状等方面,对微型涡轮喷气发动机20世纪50年代以来的发展情况进行了综述,可为今后国内研制高性能微型涡轮喷气发动机提供参考。随着进一步降低成本、提高推重比,微型涡轮喷气发动机将有更强的竞争力和更广的发展前景。To provide superior and reliable power for micro and small aerial vehicles, the micro turbojet engines have become a global researchful focus with the thrust less than 100 daN. The micro turbojet engines have the advantages of small size, high rotating speed, fewer parts, longer running time, variable thrust, lower infrared radiation value and repeated usage. The thrust-weight ratio exceeded 11.0. They have been equipped on un- manned combat aerial vehicles, targets for air defense weapons, precision-guided missiles and test vehicles. The development situation of micro turbojet engines since 1950s is reviewed and summarized in this paper, including research institutions, well-known products, main features and application status. The study can provide references for the future domestic research work on advanced micro turbo engines. With the further reduction of cost and improvement on thrust-weight ratio, the stronger competitiveness and broader development prospect of the micro turbojet engine will be achieved.

关 键 词：航空发动机 涡轮喷气 微型 技术参数 应用 

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]