A numerical study of the rapid deflagration-to-detonation transition

This paper describes numerically the rapid deflagration-to-detonation transition (DDT) in detail a high-frequency pulse detonation rocket engine. Different from traditional DDT, reactants are injected into chamber near open end and travel toward closed end. Previous experiments have implied that gasdynamic shock by injecting confined space intensive turbulence generated high-speed jet play important roles initiation, but explanations of how, when, where is were not presented clearly due to limitation experimental observation. In this work, high-resolution two-dimensional simulations performed investigate process employing physical model similar configuration. A new mechanism manifesting itself as complicated vortex–flame interaction found for flame laminar compressible or choking regime. It discovered shock, after reflecting wall, triggers through gradient reactivity with hot spot formed collision flame. dimensionless criterion defined ratio acoustic speed inverse ignition delay time applied further describe spontaneous wave propagation perspective chem-physical dynamics. quantitatively gives good prediction propagating mode subsonic deflagration developing detonation, even such complex scenario encountered work.