Study of the Effect of Shock Wave on Fuel Injection and Combustion

冲击波对燃油喷射和燃烧影响的研究

• 批准号: 14350505
• 负责人: NIIOKA Takashi
• 金额: $ 9.15万
• 依托单位: TOHOKU UNIVERSITY
• 依托单位国家: 日本
• 项目类别: Grant-in-Aid for Scientific Research (B)
• 财政年份: 2002
• 资助国家: 日本
• 起止时间: 2002 至 2003
• 项目状态: 已结题
• 来源: https://kaken.nii.ac.jp/en/grant/KAKENHI-PROJECT-14350505/
• 关键词: Shock Wave; Supersonic Combustion; Scramiet; Hydrogen Injection

To clarify the phenomena of the interaction between shock wave and combustion in scramjet engine combustors at low Mach numbers, the fundermental research was performed experimentally and numerically flame-holding characteristics of hydrogen injected vertically to the wall surface. The following results ware obtaind :1.When the shock wave was introduced in the upstream of injection slit, the position of the detached shock wave moved to the upstream. As a result, we could hold the flame even at low total temperatures and injection pressures.2.The LU-SGS method was improved to be made in parallel imaginarily by a discrete region method.3.Numerical results were qualitatively consistent with experimental ones. Since the most hydrogen stayed in the downstream detached region and reacted there, the incident shock wave introduced in the downstream detached region was more effective compared with the case introduced in the upstream of the injection slit, when the equivalence retio was small and the hydrogen temperature was low. The flame-holding in the latter case, however, could not be analyzed completely because of complex turbulent diffusion.4.By changing from the two-dimensional fuel slit jet to a single circular slot jet, fuel injection pressure could be raised without thermal choke. Also, a new measurement method of supersonic flows was developed by linking PTV with CFD.

为了阐明低马赫数下超燃冲压发动机燃烧室中激波与燃烧相互作用的现象，对垂直喷氢的火焰稳定特性进行了实验和数值研究。结果表明：1.当激波从喷射缝上游引入时，脱体激波的位置向上游移动。结果表明，在较低的总温和喷射压力下，该方法仍能保持火焰稳定; 2.采用离散区域法对LU-SGS方法进行了改进，使其并行化; 3.数值结果与实验结果定性一致。由于大部分氢停留在下游分离区并在那里反应，当当量比小且氢温度低时，在下游分离区引入的入射激波比在喷射狭缝上游引入的入射激波更有效。但后者的火焰稳定性由于湍流扩散的复杂性而不能完全分析。4.将二维燃料狭缝射流改为单圆狭缝射流，可以在不发生热阻塞的情况下提高燃料喷射压力。将PTV与CFD相结合，发展了一种新的超声速流场测量方法。

项目成果

T.Niioka ほか: "Combustion of Hydrogen Jet with the Introduction of Shock Wave in a Supersonic Air Stream"4^<th> Japan Korea Seminar on Combustion and Heat Transfer. 4. 21-21 (2003)

T. Niioka 等人：“在超音速气流中引入冲击波的氢射流燃烧”第 4 届日韩燃烧和传热研讨会。 4. 21-21 (2003)。

T.Niioka, et al.: "The effect of Shock Wave on Hydrogen Injection and Combustion in Supersonic Flow"41th Combustion Symp.. Vol.41. 281-282 (2003)

T.Niioka 等人：“冲击波对超音速流中氢气注入和燃烧的影响”41th Combustion Symp.. Vol.41。

T.Niioka ほか: "Combustion of Hydrogen Jet with the Introduction of Shock Wave"19^<th> Int. Colloquium on the Dynamics of Explosion and Reactive Systems. (発表予定). (2003)

T. Niioka 等人：“引入冲击波的氢射流燃烧”第 19 届爆炸和反应系统动力学研讨会（即将发表）。

新岡 嵩 ほか: "超音速流における水素垂直噴射および燃焼場に対する衝撃波の影響"第41回燃焼シンポジウム. 41. 281-282 (2003)

Takashi Niioka 等人：“超音速流中的垂直氢喷射和冲击波对燃烧场的影响”第 41 届燃烧研讨会 (2003)。

T.Niioka, et al.: "Combustion of Hydrogen Jet with the Introduction of Shock Wave"19th Int. Colloquium on the Dynamics of Explosion and Reactive Systems. Vol.9. 28-30 (2003)

T.Niioka 等人：“引入冲击波的氢喷射燃烧”19th Int。