Physical Hypothesis for the Combustion Instability in Cryogenic Liquid Rocket Engines
Physical Hypothesis for the Combustion Instability in Cryogenic Liquid Rocket Engines
复制标题
低温液体火箭发动机燃烧不稳定性的物理假说
DOI：
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发表时间：
2010
期刊：
影响因子：
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通讯作者：
B. Chehroudi
中科院分区：
文献类型：
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作者：
B. Chehroudi
在这项工作中，作者想描绘一个流体动力学图片的草图来描述腔室声学和喷射器之间的耦合性质/强度。这种新的观点是通过一个物理直观的参数结合先前公布的两个流行的喷射器设计，即同轴和冲击射流的测试结果。对于冲击射流喷射器，它示出的动态行为的暗核心（或破碎）区为每个射流，它们的长度和厚度，有一个深刻的影响喷射器的灵敏度在其周围的扰动。该信息用于对撞击射流喷射器中的休伊特稳定性图上所见的趋势提供可能的解释。
In this work, the author would like to portray a sketch of a fluid dynamical picture to describe the coupling nature/ strength between the chamber acoustics and the injectors. This new perspective is achieved through a physically intuitive argument combined with previously published test results for two popular injector designs, namely, coaxial and impinging jets. For the impinging jet injectors, it is shown that the dynamic behavior of the dark-core (or breakup) zone for each jet, their lengths and thicknesses, has a profound impact on injector sensitivity to disturbances in its surrounding. This information is used to offer a possible explanation for the trends seen on the Hewitt stability plot in impinging jet injectors.