Abstract
The mixing and combustion processes in a liquid oxygen/gaseous hydrogen rocket combustor were studied. The research focused on observations of atomization phenomena during steady-state combustion and ignition transients of a rocket engine. Cold-e ow atomization as encountered before ignition has been studied using liquid oxygen/gaseous hydrogen and simulation e uids liquid nitrogen/helium. The theoretical assessments show that for binary- and multicomponentsystems atranscriticalregion existswheresurfacetension ispresenteven atpressures above the critical pressure of one component as long as the critical mixing temperature is not exceeded. Also, hote retestsutilizing liquid oxygen/gaseoushydrogen demonstratethestrong ine uenceofthee ameon theatomization process.Thee amepropagation duringignitioncouldbeidentie edbythechangeoftheatomizationphenomenology before and during the ignition process. Nomenclature da = outer diameter di = inner diameter Pr = reduced pressure p = pressure T = temperature u, v = velocity π = chemical potential Ω = density ae = surface tension Subscripts c = chamber crit = critical gas = gas i = specie liq = liquid s = saturation
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