Numerical simulation is performed and compared with a firing test of an hybrid rocket engine equipped with a catalyzer. The simulation is performed assuming an axisymmetric flow, unsteady Reynolds-averaged Navier–Stokes equations are solved based on a single-phase flow. Stable pressure oscillations are observed during the firing test and could be explained by the simulation with the formation of large-scale vortices at the end of the fuel grain and in the postcombustion chamber. These vortices transport unburnt fuel to the nozzle and play a major role in the mixing process in the postchamber. Two semi-empirical approaches are applied and provide a good order of magnitude for the frequency and frequency shift during the firing test. Another simulation has been performed with an added oxidizer postchamber injection. It revealed that small-scale vortices along the fuel grain in the baseline case are probably generated by the oscillatory motion of the flow due to pressure fluctuations in the engine.
Vortex Shedding Influence on Hybrid Rocket Pressure Oscillations and Combustion Efficiency
Journal of Propulsion and Power ; 32 , 6 ; 1386-1394
2016-06-03
9 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Vortex Shedding Influence on Hybrid Rocket Pressure Oscillations and Combustion Efficiency
Online Contents | 2016
|Vortex Shedding Influence on Hybrid Rocket Pressure Oscillations and Combustion Efficiency
Online Contents | 2016
|Vortex shedding in solid rocket motors
AIAA | 1995
|