国外并联式涡轮基组合循环发动机技术发展途径浅析  

Study on the development approach of foreign over/under TBCC engine technology

作　　者：陈博 桂丰 李茜 康玉东 CHEN Bo;GUI Feng;LI Qian;KANG Yu-dong(Equipment Department of PLA Air Force,Beijing 100843,China;AECC Sichuan Gas TurbineEstablishment,Chengdu 610500,China)

机构地区：[1]中国人民解放军空军装备部,北京100843 [2]中国航发四川燃气涡轮研究院,成都610500

出　　处：《燃气涡轮试验与研究》2019年第1期57-62,共6页Gas Turbine Experiment and Research

摘　　要：为借鉴国外并联式涡轮基组合循环(TBCC)发动机技术研究经验,从飞行器使用需求出发,分析了并联式TBCC发动机面临的技术挑战,并从高速涡轮基技术、冲压发动机技术和组合技术三个方面,梳理了美国典型并联式TBCC发动机的研发计划。在此基础上,分析并提出了并联式TBCC发动机技术发展途径:拓展涡轮基工作马赫数上限和冲压发动机工作马赫数下限以实现并联式TBCC发动机模态转换,采用射流预冷技术扩展现有涡轮工作包线是短期内实现性较好的技术验证途径,开发高速涡轮发动机技术是未来发展的必然趋势。In order to learn the research experience of foreign over/under Turbine-Based Combined-Cycle (TBCC) engine technology, based on the operation requirements of flight vehicle, the technology challenges of TBCC engine were analyzed. From the aspects of high speed turbine engine technology, ramjet engine technology and combined technology, typical American over/under TBCC engine research plans were ana. lyzed. On this basis, the technology development approach of over/under TBCC engine is proposed. The ex. panding of upper limit of turbine engine working Mach number and the expanding of lower limit of ramjet engine working Mach number are applicable ways to realize the mode transition of over/under TBCC engine. The MIPCC (Mass Injection Pre-Compression Cooling Engine) technology is one appropriate approach to re. alize technology validation in the short term while the development of high speed turbine engine is required in future.

关 键 词：航空发动机 高超声速 TBCC 模态转换 高速涡轮发动机 冲压发动机 技术途径 

分 类 号：V236[航空宇航科学与技术—航空宇航推进理论与工程]