Shock Induced Combustion and Flame Folding in Supersonic Combustion Ramjet Engine

超音速冲压冲压发动机中的冲击诱发燃烧和火焰折叠

• 批准号: 13650960
• 负责人: ARAI Takakage
• 金额: $ 2.24万
• 依托单位: MURORAN INSTITUTE OF TECHNOLOGY
• 依托单位国家: 日本
• 项目类别: Grant-in-Aid for Scientific Research (C)
• 财政年份: 2001
• 资助国家: 日本
• 起止时间: 2001 至 2002
• 项目状态: 已结题
• 来源: https://kaken.nii.ac.jp/grant/KAKENHI-PROJECT-13650960/
• 关键词: Scramjet; Supersonic Combustion; Shock Induced Combustion; Supersonic Mixing; Flame Holding; Shock Tunnel; High Enthalpy Flow; Space Transportation System; デトネーション; 高エンタルピ流れ

This research was primarily concerned with flows and combustion phenomena in Scramjet engine model. Hypersonic flow was obtained by using small high enthalpy shock tunnel. At Mach number of about 7, Scramjet engine model was set in the test section. At first, the oblique-shock compression process was studied. Gaseous H2 or He were injected with the injection angle of 70 degrees to the supersonic cross flow from intake wall. We conducted Schlieren-image visualization and wall static pressure measurements, self-emission observation. Schlieren-image visualization and self-emission were observed by using CCD camera and high-speed video camera. We verified the supersonic combustion and shock-induced combustion.And also, the evaluation of supersonic mixing was conducted by using catalytic reaction on platinum wire surface. This method was applied to evaluate the time variation of hydrogen concentration in the mixing layer. The results showed that the strength of the correlation between the time variations of the hydrogen concentration and velocity in the mixing layer was effected by mixing conditions.

本文主要研究超燃冲压发动机模型内的流动和燃烧现象。利用小型高焓激波风洞获得了高超声速流场。在马赫数约为7时，将超燃冲压发动机模型置于试验段。首先，研究了冲击压缩过程。气态H2或He以70度的喷射角从进气道壁喷射到超声速横流中。进行纹影图像可视化、壁面静压测量、自发射观察。利用CCD摄像机和高速摄像机观察了薄膜的纹影显现和自发光现象。验证了超声速燃烧和激波诱导燃烧，并利用铂丝表面催化反应对超声速混合进行了评价。该方法被应用于评估混合层中的氢浓度的时间变化。结果表明，混合层中氢气浓度与速度随时间变化的相关性强弱受混合条件的影响。

项目成果

T. ARAI, J. KASAHARA, T. KOKUBO, K. MUKAI: "Study on Flows and Combustion Phenomena in Scramjet Engine Used by a Small Scale High Enthalpy Shock Tunnel (in Japanese)"Memories in Muroran Institute of Technology. No. 52. 77-84 (2001)

T. ARAI、J. KASAHARA、T. KOKUBO、K. MUKAI：“小型高焓激波隧道使用的超燃冲压发动机中的流动和燃烧现象研究（日语）”室兰工业大学的回忆。

F.SAKIMA: "Time-Series Evaluation of Hydrogen-Air Supersonic Mixing Layer by Using Catalytic Reaction"Work-in-Progress Posters at The 29th Symposium on Combustion. 12-1312 (2002)

F.SAKIMA：第 29 届燃烧研讨会上的“利用催化反应对氢-空气超音速混合层进行时间序列评估”工作进展海报。

杉山 弘: "室蘭工業大学新設マッハ4超音速風洞の気流特性および衝撃波と乱流境界層の干渉現象に関する研究"室蘭工業大学紀要. 51号. 57-62 (2001)

Hiroshi Sugiyama：“室兰工业大学新建立的4马赫超音速风洞中的气流特性及冲击波与湍流边界层之间的干涉现象的研究”室兰工业大学通报51、57-62（2001）。

Fei HE: "The Interaction between a Sonic Jet injected normal into Supersonic Cross Flow and developing Wall Boundary Layer"The 4th Asian-Pacific Conference On Aerospace Technology and Science, APCATS'2002. (2002)

何飞：“超声速射流正常注入超音速横流与发展壁边界层之间的相互作用”第四届亚太航空航天技术与科学会议，APCATS2002。

咲間文順: "超音速流中に垂直に噴出する音速噴流の挙動"室蘭工業大学紀要. 51号. 63-68 (2001)

Fumijun Sakima：“超音速流中垂直喷射的音速射流的行为”室兰工业大学通报第 51. 63-68 (2001)。