Performance comparison between the ramp injectors with different structures in supersonic combustion

WU Hai-yan; ZHOU Jin; WANG Hong-bo; SUN Ming-bo; ZHANG Shun-ping

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Performance comparison between the ramp injectors with different structures in supersonic combustion

更新时间：2026-07-07

- Performance comparison between the ramp injectors with different structures in supersonic combustion
- Vol. 24, Issue 7, (2009)
- 作者机构：
  
  国防科技大学航天与材料工程学院,长沙,410073
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2009
- 稿件说明：
移动端阅览
WU Hai-yan, ZHOU Jin, WANG Hong-bo, et al. Performance comparison between the ramp injectors with different structures in supersonic combustion[J]. 2009, 24(7).
DOI：

WU Hai-yan, ZHOU Jin, WANG Hong-bo, et al. Performance comparison between the ramp injectors with different structures in supersonic combustion[J]. 2009, 24(7). DOI：

摘要

为了进一步研究斜坡结构特点对超声速流场混合增强作用

设计了膨胀型和压缩型两种斜坡实验件

并分别进行了火焰传播、纹影及油流谱实验.利用数值仿真的方法对斜坡后压力分布、激波间相互作用以及流向涡的卷起过程进行了分析研究

与实验结果对比一致.最后分析了实验结果与国外相关研究的差异

论证了该设计的两种斜坡喷注器中膨胀型斜坡有更好的自燃及火焰稳定作用.

Abstract

The compression and expansion ramps were designed to study the mixing performance of the different structured ramp injectors.The experiments of flame transfer

schlieren photograph and oil flow were conducted for the ramp injectors.The calculation fluid dynamics was used to simulate the pressure distribution

the interaction of shock and the forming of stream eddies following the ramps injection.The simulation results are coincident with the experiments.Finally

the differences between this experiment and the previous reports were analyzed.It's concluded that the expansion ramp of the two injectors has better performance of self-ignition and flame holding than the compression one.

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Related Author

WU Hai-yan

ZHOU Jin

SHAO Yan

ZHANG Shun-ping

YE Jiawei

ZHANG Shunping

YU Xin

SHAO Yan

Related Institution

College of Aerospace and Materials Engineering, National University of Defense Technology

Sichuan Gas Turbine Establishment，Aero Engine Corporation of China

北京航空航天大学能源与动力工程学院

国防科技大学高超声速冲压发动机技术重点实验室

国防科技大学航天科学与工程学院

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