Hongbo LU, Hengyi WU, Jian LIN, Ruiting WANG, Feng JI, Xing CHEN

DOI Number: XXX-YYY-ZZZ

Conference number: HiSST 2024-0091

To promote the efficiency of highly supersonic combustion of high Mach number scramjets, this study highlighted the crucial role of the flame stabilization and heat release enhanced by the cavity-aft shock pattern. A three-dimensional scramjet model was designed, which included a combustor with a constant width and a symmetrical-configured-cavity. The combustion characteristics of the hydrogen jet upstream of the cavity in the highly supersonic crossflow were investigated using OH* chemiluminescence combined with wall pressure measurements at the nominal simulated condition of Ma10 in FD-21 high enthalpy shock tunnel. The evolution of hydrogen combustion, flame-stabilization structure, and heat release characteristics are presented. From the dynamic characteristics of OH* emission, it is found that the so-called “shock tube flow-combustion” mechanism is formed at the immediate moment when the freestream flow entering the scramjet, due to the employment of the fuel injection before the arrival of the mainstream crossflow. This mechanism results in an absolutely different ignition mechanism from the one during the process of fuel injection after the crossflow absolutely establishes. In spite of this phenomenon, the flame still stabilizes in the bodyside jet wake and the whole flowpath height around the cavity aft under the coupling effect of the self-ignition from the high total temperature and cavity-aft X-type shock pattern when the interaction of fuel jet with the highly supersonic crossflow tends to a quasi-steady regime. The wall pressure rise characteristics induced by heat release reveals that the combustion inside the engine is in a pure supersonic combustion mode, and a maximum heat release rate occurs around the cavity, indicating the combustion is enhanced by the cavity-aft X-type shock pattern. These results of cavity-aft-shock enhanced combustion in a Ma10 supersonic combustor can be aid in design of high-performance combustion for high Mach number scramjets.

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In Categories: 1.Events, HiSST 2024, Propulsion Systems and Components
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