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Combustion Dynamics in Postchamber of Hybrid Rocket Using CH* Radical Chemiluminescence Images

机译:CH *自由基化学发光图像在混合火箭后室燃烧动力学

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摘要

A series of tests are conducted to understand the basic features of the coupling mechanism of combustion pressure with the local heat release fluctuation upon the occurrence of low-frequency instability in a hybrid rocket engine. In stable combustion, combustion pressure fluctuates at the frequency of about 20 Hz because of the thermal lag of solid fuel burning. Also, there exist steady spatial distributions of heat release, which are similar to a shear-layer structure. However, when low-frequency instability occurs, the combustion pressure is amplified, and the luminosity starts to fluctuate at a frequency of about 20 Hz. More interestingly, a positive coupling is observed between two fluctuations. The CH* radical luminosity images and proper orthogonal decomposition analysis show the lumped flow structures with time-varying intensity in unstable combustion. A periodic change in the local heat release appears to generate large-scale flow rotations, and the large-scale flow rotations are likely to be associated with the periodic flame extinction at a frequency of about 20 Hz. Also, the flame extinction seems to take a crucial role in the occurrence of low-frequency instability, although it is not clearly understood why the flame extinction occurs in the specific geometric configuration.
机译:进行了一系列测试,以了解混合动力火箭发动机发生低频不稳定性时燃烧压力与局部放热波动的耦合机制的基本特征。在稳定燃烧中,由于固体燃料燃烧的热滞后,燃烧压力以大约20 Hz的频率波动。同样,存在稳定的热量释放空间分布,类似于剪切层结构。然而,当发生低频不稳定性时,燃烧压力增大,并且发光度开始以大约20Hz的频率波动。更有趣的是,在两个波动之间观察到正耦合。 CH *自由基发光度图像和适当的正交分解分析显示了不稳定燃烧中集流结构随强度的变化。局部放热的周期性变化似乎会产生大规模的旋流,并且大规模的旋流可能与大约20 Hz的周期性火焰熄灭有关。另外,尽管对于为什么火焰熄灭以特定的几何构型发生,尚不清楚,但火焰熄灭在低频不稳定性的发生中起着至关重要的作用。

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  • 来源
    《Journal of propulsion and power》 |2017年第1期|176-186|共11页
  • 作者单位

    Hanwha Corporation, Daejeon 305-156, Republic of Korea;

    Konkuk University, Seoul 143-801, Republic of Korea;

    Konkuk University, Seoul 143-801, Republic of Korea;

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