A supersonic combustion in a Laval nozzle
Hi to all,
As a part of my diploma thesis I have to analyze the DDT (deflagration to detonation transition) phenomena. I choose a Laval nozzle geometry to simulate a gas acceleration from the subsonic to supersonic flow also using coupled - implicit solver. Already done. My point is, that when I was trying to simulate a hydrogen-air combustion using species transport (Eddy-dissipation) as a species model there was no H2+O2 reaction in the nozzle at all. :confused: Where did I go wrong? Im I right when I think that I have to use the Premixed Combustion model? But then I have to choose the segregated solver. It is possible to solve the supersonic flow with segregated solver? Excuse me for my bad English. Many thanks.
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