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Experimental and numerical study of transcritical oxygen-hydrogen rocket flame response to transverse acoustic excitation
Proceedings of the Combustion Institute ( IF 3.4 ) Pub Date : 2020-10-20 , DOI: 10.1016/j.proci.2020.05.027
Scott K. Beinke , Justin S. Hardi , Daniel T. Banuti , Sebastian Karl , Bassam B. Dally , Michael Oschwald

The response of a transcritical oxygen-hydrogen flame to transverse acoustic velocity was investigated using a combination of experimental analyses and numerical modelling. The experiment was conducted on a rectangular rocket combustor with shear coaxial injectors and continuously forced transverse acoustic field. Simultaneous high-speed shadowgraph and filtered OH* radiation images were collected and reduced using dynamic mode decomposition in order to characterise the flame response to the acoustic disturbance. CFD modelling of a representative single injector under forcing conditions was carried out to gain insights into the three-dimensional features of the reacting flow field. Invisible in the 2D projection, the model reveals that the excited LOX jet develops into a flattened and widened structure normal to the imposed acoustic velocity. The comparison of co-located structures allowed features in the imaging to be attributed to the deformation and transverse displacement of lower density oxygen surrounding the denser liquid oxygen core by the transverse acoustic velocity.



中文翻译:

跨临界氧氢火箭对横向声激发的火焰响应的实验和数值研究

结合实验分析和数值模拟研究了跨临界氧氢火焰对横向声速的响应。该实验是在带有剪切同轴喷射器和连续受力横向声场的矩形火箭燃烧器上进行的。使用动态模式分解来收集和减少同时的高速阴影图和已过滤的OH *辐射图像,以表征火焰对声干扰的响应。在强制条件下,对代表性的单喷油嘴进行了CFD建模,以深入了解反应流场的三维特征。该模型在2D投影中不可见,它揭示了激发的LOX射流发展成垂直于所施加声速的平坦和加宽的结构。

更新日期:2020-10-20
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