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- W2334693160 abstract "The general view of the atomization process for gas/liquid shear-coaxial rocket engine injectors envisions a relatively short intact liquid core from which ligaments or drops are continually shed due to surface instabilities. At some point in the process, the presence of the intact liquid core ceases and only the drop field remains. This classical phenomenological breakup model indicates that the progress of liquid atomization depends primarily on the momentum flux and/or velocity ratios between the gas and liquid streams. Recent rocket combustion research experiments at gas-to-liquid momentum flux ratios (J) of about one to five had cast doubt on this breakup/atomization model for some typical injection conditions. Some rocket engines, such as the Ariane 5 Vulcain, run injectors at higher momentum fluxes (J ≈ 10-11). To evaluate the applicability of the core-stripping spray model at even extreme conditions for rocket applications, liquid oxygen (LOX) / gaseous hydrogen (GH2) combustion experiments were carried out at much higher momentum flux values (J ~ 22 and 50). A shadowgraph imaging technique was applied to record the LOX jet structure at various axial locations from which LOX dense-core length measurements were made. LOX core lengths were found to scale with the inverse of momentum flux; however, the flowfield even at J > 20, exhibits a long sinuous LOX core region, eventually breaking up into large LOX structures that gasify in the core wake. This LOX core fragmentation process seems to dominate the primary atomization process even at very high momentum flux ratios. Several existing core length correlations, none of which were developed under combustion conditions, were examined for applicability to realistic rocket engine conditions." @default.
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- W2334693160 date "2006-07-09" @default.
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- W2334693160 title "LOX/GH2 Shear Coaxial Injector Atomization Studies at Large Momentum Flux Ratios" @default.
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- W2334693160 doi "https://doi.org/10.2514/6.2006-5203" @default.
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