超燃冲压及TBCC组合循环发动机尾喷管设计方法研究进展  

Research Progress of Nozzle Design Method for Scramjet and Turbine Based Combined Cycle

作　　者：徐惊雷[1] XU Jing-lei(Jiangsu Province Key Laboratory of Aerospace Power System,College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学能源与动力学院、江苏省航空动力系统重点实验室,江苏南京210016

出　　处：《推进技术》2018年第10期2236-2251,共16页Journal of Propulsion Technology

摘　　要：随着对远程、宽马赫数范围内高速飞行器的需求日益迫切,超燃冲压发动机(Scramjet)、甚至未来涡轮基组合循环发动机(Turbine Based Combined Cycle,TBCC)等已成为国内外研究的焦点。推进系统是高超声速飞行器能否实现宽马赫数范围内高效工作的关键,而非对称喷管(Single Expansion Ramp Nozzle,SERN)是其重要组成部分和关键技术之一。本文主要分析了远程、宽马赫数范围内高速飞行器对其发动机尾喷管的特殊要求,简要回顾了国内外相关的研究进展,重点介绍了本课题组针对超燃冲压及组合循环发动机尾喷管设计方法的主要工作和研究进展。结果表明:在大落压比下,不同的设计方法对非对称喷管的气动性能,特别是升力和俯仰力矩影响较大。最后对未来的研究进行了展望,旨在总结目前的相关研究进展,梳理关键科学与技术问题,为后续的研究工作提供参考。With increasing urgent demand of long-range and wide-range Mach number high speed vehicle,Scramjet,even Turbine Based Combined Cycle（TBCC）,etc.,have become the research focus all over the world.Propulsion system is the key of hypersonic vehicle to achieve high efficiency in wide operation corridor,and Single Expansion Ramp Nozzle（SERN）is one of the most important parts and key technologies of propulsion system. The special requirements of the exhaust nozzle for long-range and wide-range Mach number high speed vehicle are analyzed,the relative progress all around the world is reviewed briefly,the main work and research progress of the design method for scramjet nozzle and TBCC exhaust system by our group are mainly introduced. The results show that the SERN profiles designed by different method have great effects on the aerodynamic performances of nozzle under high Nozzle Pressure Ratio（NPR）. Finally,the future research project is proposed. This paper is aimed at concluding the recent research progress,analyzing the key problem of science and technology,and providing the reference and suggestions for the future research.

关 键 词：超燃冲压发动机 涡轮基组合循环发动机 非对称喷管 设计方法 评述 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]