超声速气流中的斜爆震研究进展综述

苗世坤; 周进; 刘彧; 刘世杰; 林志勇

doi:10.11729/syltlx20180078

超声速气流中的斜爆震研究进展综述

doi: 10.11729/syltlx20180078

苗世坤^1,,
周进^1, ,,
刘彧²,
刘世杰¹,
林志勇¹

1.
国防科技大学高超声速冲压发动机技术重点实验室, 长沙 410073
2.
中国空气动力研究与发展中心高超声速冲压发动机技术重点实验室, 四川绵阳 621000

基金项目:

国家自然科学基金项目 91441101

国家自然科学基金项目 11702316

详细信息

作者简介:
苗世坤(1989-), 男, 江苏徐州人, 博士研究生。研究方向:高超声速推进技术。通信地址:湖南省长沙市开福区德雅路109号湖南省长沙市开福区德雅路109号(410073)。E-mail:miaoshikun@nudt.edu.cn

通讯作者:
周进, E-mail:zj706@vip.sina.com

中图分类号: V231.2
计量
- 文章访问数: 378
- HTML全文浏览量: 163
- PDF下载量: 36
- 被引次数: 0
出版历程
- 收稿日期: 2018-05-22
- 修回日期: 2018-06-06
- 刊出日期: 2019-02-25

Review of studies on oblique detonation waves in supersonic flows

1.
Science and Technology on Scramjet Laboratory, National University of Defense Technology, Changsha 410073, China
2.
Science and Technology on Scramjet Laboratory of Hypervelocity Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China

摘要

摘要: 对超声速气流中斜爆震波的起爆和驻定特性的研究进展进行总结，重点回顾了斜爆震波起爆准则和驻定条件的实验研究。随后对斜爆震过渡区结构及波面胞格结构的研究历程和发展现状进行了概述。此外，对爆震波与湍流边界层相互作用的研究现状进行概述，分析总结了当前斜爆震研究存在的问题，对后续的斜爆震研究内容和研究手段提出建议。
- 超声速推进 /
- 斜爆震起爆 /
- 驻定 /
- 过渡区结构 /
- 胞格结构
Abstract: The research progress and development status of studies on oblique detonation waves in supersonic flows are summarized. Experimental investigations on the initiation and stability of oblique detonation waves are firstly provided, especially on the initiation criterion and the formation condition of different transition structures. Then studies on the transition structure and the cellular structure are reviewed, where the effects of the inflow condition and the wedge angle on the wave structures are introduced. Besides, studies on the interaction between the oblique detonation wave and the turbulence boundary layer are reviewed. Some challenges in current studies are analyzed and some suggestions on future studies on oblique detonation waves are given.
- supersonic propulsion /
- initiation of oblique detonation /
- stability /
- transition structure /
- cellular structure

HTML全文

图 1 斜爆震发动机(a)及飞行器整体(b)结构示意图^[30]

Figure 1. Schematic view of (a) a supersonic ramjet with oblique detonation wave and (b) an engine integrated into a hypersonic plane^[30]

下载: 全尺寸图片幻灯片

图 2 高速射弹引起的激波诱导不稳定燃烧阴影图^[48]

Figure 2. Shadowgraph of shock-induced combustion on supersonic projectile^[48]

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图 3 不同工况下高速射弹产生的不同燃烧机制:(a)直接斜爆震波, (b)延迟斜爆震波, (c)、(d)不稳定燃烧机制, (e)波分离机制, (f)惰性激波^[67]

Figure 3. Different combustion regimes under different conditions: (a) prompt ODW, (b) delayed ODW, (c), (d) combustion instability, (e) wave splitting, (f) inert shock wave^[67]

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图 4 理论起爆极限与实验结果的比较^[67]

Figure 4. Comparison between the theoretical limits and the experimental results^[67]

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图 5 斜爆震波的"Straw Hat"结构流场阴影图^[72]

Figure 5. Shadowgraphs of "Straw Hat" structure of oblique detonation waves^[72]

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图 6 不同过渡区结构的斜爆震流场示意图^[80]

Figure 6. Schematic of ODWs with different transition structures^[80]

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图 7 斜激波管中得到的斜爆震波纹影(a)和PLIF图像(b); OSW:斜激波, ODW:斜爆震波, TW:横波, OF:倾斜火焰^[104]

Figure 7. Schlieren and PLIF images of delayed oblique detonation wave. OSW: oblique shock wave; ODW: oblique detonation wave; TW: transverse wave; OF: oblique flame^[104]

下载: 全尺寸图片幻灯片

图 8 斜爆震流场中的激波边界层相互作用示意图^[140]

Figure 8. Schematic of shock/boundary layer interaction in ODW flowfield^[140]

下载: 全尺寸图片幻灯片

图 9 超声速风洞中在中等边界层分离区尺度下得到的间歇突跃-平滑型的斜爆震波^[141]

Figure 9. Intermittent abrupt-delayed oblique detonation wave under moderate scales of boundary layer separation in a supersonic wind tunnel^[141]

下载: 全尺寸图片幻灯片

表 1 爆震燃烧与爆燃燃烧对比^[34]

Table 1. Comparison between deflagrative combustion and detonative combustion^[34]

	爆燃燃烧	爆震燃烧
1	火焰传播速度为几十米每秒量级，燃烧室尺寸较大	爆震传播速度为千米每秒量级，燃烧区域小，燃烧室尺寸更小
2	在高当量比条件下燃烧，高温、释放更多NO_x，需要在涡轮前提供额外的空气	贫燃燃烧(火箭基富燃)，低温。释放较少NO_x，不需要提供额外的空气
3	燃烧波导致压力降低	爆震波后压力急剧升高
4	设计复杂	设计简单

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