航空发动机

芮长胜1 ，武郁文 2 ，王晓东 1 ，李群2 ，姜海龙 1 ，翁春生 2.旋转爆震燃烧航空涡轮发动机研究综述[J].航空发动机,2023,49(2):1-12

旋转爆震燃烧航空涡轮发动机研究综述

Review of Research on Rotating Detonation Turbine Engine

DOI：

英文关键词:rotating detonation combustion turbine engine propulsion system research status key technology

基金项目:军科委基础加强课题（2019-JCJQ-ZD-033-00）资助

作者	单位
芮长胜1 ，武郁文 2 ，王晓东 1 ，李群2 ，姜海龙 1 ，翁春生 2	1. 中国航发沈阳发动机研究所，沈阳 110015；2. 瞬态物理国家重点实验室，南京 210094

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中文摘要:

旋转爆震燃烧具有燃烧过程自增压、熵增小、循环热效率高等特性，将其应用于航空涡轮发动机，有望实现发动机性能阶跃式突破。主要介绍了旋转爆震燃烧的基本原理及特点，总结了国内外旋转爆震燃烧技术、旋转爆震涡轮发动机性能和试验技术的研究现状，论述了旋转爆震燃烧加快应用到航空涡轮发动机上需要深化研究宽范围进气下稳定爆震燃烧组织、旋转爆震燃烧与上下游匹配等关键技术，并对中国旋转爆震燃烧航空涡轮发动机工程化应用提出了制定长期发展规划、实施专项研究计划、组建联合团队等发展建议。

英文摘要:

As the rotating detonation combustion has the characteristics of self-pressurization, low entropy increase and high cycle thermal efficiency, it is expected to achieve a breakthrough in engine performance when the detonation combustion was applied to aero tur? bine engine. The basic principle and characteristics of rotating detonation combustion are mainly introduced, and the research status of ro? tating detonation combustion technology, performance and test technology of rotating detonation turbine engines at home and abroad are summarized. The key technologies for accelerating the application of rotating detonation combustion to turbine engines are discussed, such as stable detonation combustion organization under a wide intake range, and matching of rotating detonation combustion with upstream and downstream components. Some suggestions are put forward for the engineering application of rotating detonation turbine engines in China, including long-term development planning, implementation of special research programs, and establishment of joint teams.

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