Numerical simulation of the supersonic turbulent reacting flow field in a dual throat- dual fuel rocket thrust chamber is presented. Future single stage to orbit and high lift space transportation missions aspire a reliable, efficient, and cost-effective propulsion systems. The dual throat-dual fuel concept is a simple altitude compensating propulsion alternative with reusable possibilities. Turbulent reacting supersonic flow field emanating from independent thrust chambers needs to be resolved for a better understanding of the flow structures and design modifications for the performance improvement. The operation of a dual throat nozzle brings about a unique shock train in reacting supersonic flow. Two-dimensional axis-symmetric compressible reacting flow field has been solved using HLLC (Harten, Lax, van Leer, with Contact wave) scheme based finite volume Riemann solver with multi-step finite rate chemistry model for hydrocarbon/hydrogen-oxygen combustion. The computational procedure has been validated with experimental data for species distribution of a coaxial supersonic combustor. Chemical species distribution in the supersonic free shear layer is analyzed in detail to explore the nature of active reaction zones in the flow field.
Jayakrishnan, S., & Deepu, M. (2020). Reacting Flow Simulations of a Dual Throat-Dual Fuel Thruster. Journal of Applied Fluid Mechanics, 14(1), 49-59. doi: 10.47176/jafm.14.01.31329
MLA
S. Jayakrishnan; M. Deepu. "Reacting Flow Simulations of a Dual Throat-Dual Fuel Thruster", Journal of Applied Fluid Mechanics, 14, 1, 2020, 49-59. doi: 10.47176/jafm.14.01.31329
HARVARD
Jayakrishnan, S., Deepu, M. (2020). 'Reacting Flow Simulations of a Dual Throat-Dual Fuel Thruster', Journal of Applied Fluid Mechanics, 14(1), pp. 49-59. doi: 10.47176/jafm.14.01.31329
VANCOUVER
Jayakrishnan, S., Deepu, M. Reacting Flow Simulations of a Dual Throat-Dual Fuel Thruster. Journal of Applied Fluid Mechanics, 2020; 14(1): 49-59. doi: 10.47176/jafm.14.01.31329
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