Abstract—In this numerical study, supersonic combustion of hydrogen has been presented for Mach 2. The combustor has a single fuel injection parallel to the main flow from the base. Finite rate chemistry model with k-ε model and Spalart-Allmaras (S-A) Model have been used for modeling of supersonic combustion. The coupled phenomena of mixing and burning cm only be numerically modeled with the inclusion of a finite-rate chemical kinetic mechanism. The main issue in supersonic combustion is proper mixing within short burst of time. Attention is paid to the local intensity of heat release, which determines, together with the duct geometry, techniques for flame initiation and stabilization, injection techniques and quality of mixing the fuel with oxidizer, the gas-dynamic flow regime. The two-dimensional mathematical model involves the k-ε and Spalarts-Allmaras turbulence model, modified for supersonic compressibility, and a detailed kinetic mechanism of mixture combustion. The five main parameters were considered like Mach number stagnation temperature, mass fraction, stagnation pressure and velocity. The result shows the better mixing of fuel and the flame speed increases almost linearly. The stagnation temperature in the combustion reaches up to 2820K. Fluctuation in pressure and Mach number was due to shock train.
Index Terms—flame speed, Mach number, supersonic combustion, Spalart-Allmaras, finite rate, stagnation temperature.
K. M. Pandey, Member IACSIT, Department of Mechanical Engineering, N. I. T Silchar, Assam, India (email: kmpandey2001@yahoo.com).
A. P. Singh, Member IACSIT, Department of Mechanical Engineering, N. I. T Silchar, Assam, India(email : hello2apsingh@gmail.com).
Cite: K. M. Pandey and A. P. Singh, "Numerical Analysis of Combustor Flow Fields in Supersonic Flow Regime with Spalart-Allmaras and k-ε Turbulence Models," International Journal of Engineering and Technology vol. 3, no. 3, pp. 208-214, 2011.
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