Banica M.C.,University of Stuttgart |
Banica M.C.,Institute for Aerospace Thermodynamics |
Scheuermann T.,University of Stuttgart |
Scheuermann T.,Institute for Aerospace Thermodynamics |
And 6 more authors.
Journal of Propulsion and Power | Year: 2010
Numerical studies of the flow conditions in the supersonic combustion facility of the Institute of Aerospace Thermodynamics of the Universität Stuttgart was reported. The commercial tool computational fluid dynamics (CFD++) was used for all calculations. All simulations were steady state using a Courant-Friedrichs-Lewy number of 20. Turbulence-chemistry interactions were neglected. The performance of the combustion chamber was characterized by means of two parameters. The first is the mixing efficiency nm. The results show that in strong combustion, the flame is stabilized by subsonic recirculation zones in the wake of the injector. Separated flow regions also develop in the channel corners above and below the injector leading and trailing edges. The separation around the leading edges is caused by injector displacement effects and therefore present in the absence of combustion.