摘要
吸气式推进系统是实现高超声速飞行的基石,随着对宽Ma范围内高速飞行器的需求日益迫切,涡轮基组合循环(turbine based combined cycle, TBCC)发动机等已成为国内外研究的焦点,而高效压缩的进气系统是其重要组成部分和关键技术之一。该文主要分析了宽Ma范围内高速飞行器对进气系统的特殊要求,回顾了国内外关于内转式TBCC进气道的研究进展,重点介绍了以TriJet为代表的内转式TBCC进气系统的设计方法。总结了内转式TBCC进气道所面临的主要挑战,着重介绍了这类进气道面临的独特的锥面激波/边界层干扰问题,可为后续的研究工作提供参考。
The increasing demand for air-breathing propulsion systems in hypersonic aircraft that can operate over a wide Mach number range has led to development of the turbine based combined cycle(TBCC). The high-performance compressed air intake system is a key component of these systems. This study analyzed the requirements for air intake systems of hypersonic aircraft operating over a wide Mach number range. This paper reviews research on the TBCC intake design, especially the internal rotating TBCC air intake system presented by TriJet. This review then summarizes the main challenges facing the development of the TBCC intake and the unique conical shock wave/boundary layer interactions in this intake to provide references for subsequent research work.
作者
左逢源
ZUO Fengyuan(State Key Laboratory for Strength and Vibration of Mechanical Structures,School of Aerospace Engineering,Xi'an Jiaotong University,Xi'an 710049,China)
出处
《清华大学学报（自然科学版）》
EI
CAS
CSCD
北大核心
2022年第3期555-561,共7页
Journal of Tsinghua University(Science and Technology)
基金
国家自然科学基金资助项目(12002261)
博士后创新人才支持计划项目(BX20200267)
陕西省高校科协青年托举人才项目(20200501)
博士后面上项目(2020M673411)
中央高校基本科研业务费(xzy012020096)。
