Systematic Numerical Study of the Supersonic Combustion in an Experimental Combustion Chamber

A systematic computational study has been conducted on the supersonic combustion of a hydrogen jet in the LAERTE combustion chamber, which was experimentally tested at ONERA. The fuel jet is injected at Mach 2 along the chamber axis into a hot flow of vitiated air. The conditions in the vitiated air flow are: Mach number of 2, total temperature about 1850 K. By assuming a two-dimensional axisymmetric (2DA) configuration of the combustion chamber, a broad parametric study has been performed on the following important factors: boundary conditions, computational mesh adaptation, turbulence and chemical kinetic models, air vitiation. Finally a three-dimensional (3D) simulation has been made to study the 3D effects. The 2DA and 3D simulations are carefully compared with the available experimental data to validate the computational approach. A good agreement is obtained between the simulation and experimental results.

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