Simulation numérique de la combustion dans un scramjet avec injection transversale de carburant

The evolution of the future transport at high speed will depend strongly on the development of the hypersonic propulsion engines. The combustion chamber represents one of the basic technologies which order the development of these propulsion systems. At hypersonic flight speed, the available time for either the injection of fuel, the creation of the reactive mixture air-fuel and the combustion is very short. Certain numbers of studies were carried out and various strategies of injection were suggested so that configurations of combustion chambers of Scramjets overcome the limitations imposed by the short residence time. The present study describes a numerical investigation of the performances of turbulent supersonic combustion when a transverse sonic injection of the fuel (hydrogen) through a slot nozzle in a supersonic hot air stream is employed. In order to carry out this, an in-house code (Karalis) is used. Karalis is a parallel MPI, Finite- Volume, multiblock CFD code which solves the fully compressible Euler and Navier- Stokes equations, where all couplings between dynamics and thermodynamics are allowed. This is the most general mathematical model for all fluid flows. The results obtained are compared with those provided by the literature.

@InProceedings{BTDH08,
  author       = {Belmrabet, T. and Talice, M. and Delussu, G. and hanchi, s.},
  title        = {Simulation numérique de la combustion dans un scramjet avec injection transversale de carburant},
  booktitle    = {CISM08 2eme conference internationale sur les sciences de la mecanique},
  month        = {november},
  year         = {2008},
  url          = {https://publications.crs4.it/pubdocs/2008/BTDH08},
}