超声速混合层燃烧研究进展

doi:10.7527/S1000-6893.2016.0265

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超声速混合层燃烧研究进展

陈钱^1,2, 张会强¹, 王兵¹, 周伟江², 杨云军²

1. 清华大学航天航空学院, 北京 100084;
2. 中国航天空气动力技术研究院, 北京 100074

收稿日期:2016-01-11 修回日期:2016-10-18 出版日期:2017-01-15 发布日期:2016-10-17
通讯作者: 张会强,E-mail:zhanghq@tsinghua.edu.cn E-mail:zhanghq@tsinghua.edu.cn
基金资助:
国家自然科学基金(91541206)

Research progress of combustion in supersonic mixing layers

CHEN Qian^1,2, ZHANG Huiqiang¹, WANG Bing¹, ZHOU Weijiang², YANG Yunjun²

1. School of Aerospace Engineering, Tsinghua University, Beijing 100084, China;
2. China Academy of Aerospace Aerodynamics, Beijing 100074, China

Received:2016-01-11 Revised:2016-10-18 Online:2017-01-15 Published:2016-10-17
Supported by:
National Natural Science Foundation of China (91541206)

摘要/Abstract

摘要：

超声速混合层燃烧研究是解决超声速燃烧难点的有效途径，对于超燃冲压发动机的发展具有重要意义。这一领域在过去20多年中开展了大量工作，需要对此进行总结。由于无反应超声速混合层流动特性研究是超声速混合层燃烧研究的基础，因此，首先综述了该流动特性，包括瞬时流场结构和时均统计特性；其次，讨论了着火特性，包括着火距离和着火过程；再次，综述了火焰特性，特别是火焰结构；然后，关注了熄火特性；接着，对释热和可压缩性影响进行了总结；最后，给出了燃烧不稳定性的研究进展。通过综述可知，超声速混合层燃烧研究仍需开展大量工作。在着火特性、火焰特性和熄火特性方面，后续研究可重点采用湍流数值模拟和详细反应机理，研究着火过程、火焰传播过程和熄火过程，以及流动参数、热力学参数、组分参数和外界因素对着火距离、火焰结构和熄火位置的影响；在释热和可压缩性影响方面，后续研究可采用高精度数值或实验方法，重点研究高释热和高可压缩性条件下有反应超声速混合层的瞬变特性和统计特性；燃烧不稳定性方面，后续研究可采用高精度数值或实验方法，重点研究超声速混合层燃烧不稳定性产生的普遍准则及其内在机制。

关键词: 超声速湍流, 着火, 火焰, 熄火, 释热影响, 可压缩性影响, 不稳定性

Abstract:

The research on combustion in supersonic mixing layers is an effective approach to solve the problems encountered in supersonic combustion, and hence is important for the development of the scramjet. In the past twenty years, a plenty of work has been conducted in this field, and needs to be summarized. As the research on flow properties of supersonic inert mixing layers is the foundation of the research on combustion in supersonic mixing layers, these flow properties including instantaneous flow structures and time-averaged statistic properties are reviewed. Ignition properties are discussed including ignition distance and ignition processes. Flame properties, especially flame structures, are explored. Extinction properties are considered. Heat release and compressibility effects are summarized. Advances in combustion instability are given. The review suggests that a large amount of research work on combustion in supersonic mixing layers still needs to be conducted. Regarding ignition properties, flame properties and extinction properties, future research could focus on ignition process, flame propagation process and extinction process, and the effects of flow parameter, thermodynamic parameters, species parameters and external factors on ignition distance, flame structures and extinction position, using turbulent simulation and detailed mechanisms. With respect to heat release and compressibility effects, future research could concentrate on the instantaneous properties and statistic properties of high-exothermicity and high-compressibility reacting supersonic mixing layers, using high precision numerical or experimental methods. For combustion instability, future research could be devoted to general criteria and inherent mechanisms for supersonic mixing layer combustion instability, using high precision numerical or experimental methods.

Key words: supersonic turbulent flow, ignition, flame, excitation, heat release effects, compressibility effects, instability

中图分类号:

V231.2

陈钱, 张会强, 王兵, 周伟江, 杨云军. 超声速混合层燃烧研究进展[J]. 航空学报, 2017, 38(1): 20036-020036.

CHEN Qian, ZHANG Huiqiang, WANG Bing, ZHOU Weijiang, YANG Yunjun. Research progress of combustion in supersonic mixing layers[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017, 38(1): 20036-020036.

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超声速混合层燃烧研究进展

Research progress of combustion in supersonic mixing layers

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