Abstract The initial flame kernel blow-out process in an ethylene fueled scramjet combustor with a rear-wall-expansion cavity was investigated experimentally and numerically. In the experiment, it was observed that the initial flame kernel was blew off quickly after ignition under 5 different global equivalence ratios. A high precision numerical method was then adopted and the method was validated by comparing numerical results with available experimental data. It is found that the physical process from ignition to flame complete blow-out is well simulated by the numerical solver. Based on the numerical results, the blow-out process is divided into 6 stages and the characteristics of each stage are concluded. It is analyzed that the combined effect of the cavity recirculation zone and the cavity shear layer as well as the upper mainflow reduces the retention time of the initial flame kernel before it can develop to a steady flame base, which is the reason for the unsuccessful ignition in the rear-wall-expansion cavity.
Highlights Initial flame blow-outprocess in a supersonic combustor has beencaptured. Thein-house code has successfully simulatedthe physical process. Characteristics of different stages inthe blow-out process are studied. The reason for flameblow-out in rear-wall-expansioncavity has been analyzed.
Experimental and numerical investigation on initial flame kernel blow-out in a supersonic combustor with a rear-wall-expansion cavity flameholder
Acta Astronautica ; 164 ; 358-365
2019-08-21
8 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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