斜爆震发动机研究进展与技术挑战  

Research Progress and Technical Challenges of Oblique Detonation Engines

作　　者：凌文辉[1] 周林 涂胜甲[1] 解豪品 张义宁 孟皓[1] 滕宏辉[2] LING Wenhui;ZHOU Lin;TU Shengjia;XIE Haopin;ZHANG Yining;MENG Hao;TENG Honghui(Beijing Power Machinery Institute,Beijing 100074,China;School of Aerospace Engineering,Beijing Institute of Technology,Beijing 100081,China)

机构地区：[1]北京动力机械研究所,北京100074 [2]北京理工大学宇航学院,北京100081

出　　处：《南京航空航天大学学报》2023年第4期553-572,共20页Journal of Nanjing University of Aeronautics & Astronautics

摘　　要：斜爆震发动机(Oblique detonation engine,ODE)采用驻定斜爆震波(Oblique detonation wave,ODW)实现高超声速气流中燃料化学能向推进系统机械能的高效转化,可大幅提升吸气式飞行速域上限,具有重要发展潜力和应用价值。本文从早、中、近期3个阶段概述ODE发展历程,总结当下斜爆震燃烧及发动机的研究现状。重点从发动机设计角度综述国内外在斜爆震燃烧组织、燃料喷注掺混以及总体性能与内流设计3方面的研究进展。深入分析了总体约束下的内外流一体化设计、高超声速气流中的燃料喷注掺混、复杂来流条件下的稳定燃烧组织、高热载荷防护以及超高速工况试验条件5大技术挑战及重点关注方向,为后续深入技术攻关及应用提供参考。The oblique detonation engine(ODE)utilizes standing oblique detonation wave(ODW)to efficiently convert the chemical energy of fuel into mechanical energy in hypersonic flow,greatly improving the upper limit of the air-breathing flight regime,which holds significant development potential and practical value.This paper provides an overview of the development of ODE in the early,middle,and recent stages.Then,the current research status on oblique detonation combustion and engines are summarized.Furthermore,the progress made worldwide in three areas,oblique detonation combustion organization,fuel injection mixing,and overall performance with internal flow design,are reviewed from the perspective of engine design.Finally,the technique challenges and future key focus directions in five aspects,including integrated design of internal and external flow under overall constraints,fuel injection and mixing in hypersonic flow,stable combustion organization under complex inflow conditions,high thermal load protection,and experimental conditions under ultra-high speed conditions are analyzed,aiming to provide reference for future in-depth technological breakthroughs and applications.

关 键 词：斜爆震发动机 总体性能 喷注掺混 爆震燃烧 关键技术 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]