Numerical Simulation of Hydrogen Combustion in Model SCRAMJET Combustor using IDDES framework

Abstract

The non-reactive and reactive flows through a model scramjet were investigated using a Improved Delayed Detached Eddy Simulation(IDDES), which is one of the hybrid schemes of Reynold averaged Navier-Stokes equation and large eddy simulation, and flamelet combustion model. Geometries and boundary conditions of scramjet combustor conducted by DLR, German Aerospace Center were considered. The model scramjet combustor consists of 15 holes for hydrogen injection located on the base of a wedge shaped fuel injector providing hydrogen at sonic speed. In this paper, only one of the 15 injection holes was considered, and periodic condition is applied in the spanwise dirction. The parametric studies were conducted with a view to invesitigate better numerical configurations, for example, MUSCL or WENO as convective flux schemes and k-ω SST or IDDES as turbulence models with steady flamelet combustion model. The combination of WENO and IDDES provides best one for reacting case. NomenclatureD k = turbulent kinetic energy destruction term E = specific total energy f = mixture fraction h = specific enthalpy k = turbulent kinetic energy l = length scale M t = turbulent mach number p = static pressure P k = turbulence kinetic energy production term q j = specific heat flux t = time T = temperature u = velocity x = spatial coordinate Y = species mass concentraion δ ij = Kronecker delta μ = molecular viscosity μ t = turbulent viscosity ρ = density τ ij = viscous stress tensor ω = turbulent frequency Superscripts ‾ = time averaged quantity ~ = Favre averaged quantity 1 Graduate Research Assistant, School of Aerospace and Mechanical Engineering 2 Professor, School of Aerospace and Mechanical Engineering; hgsung@kau.kr. Associate Fellow AIAA Downloaded by UNIVERSITY OF ILLINOIS on October 1, 2015 | http://arc.aiaa.org |

Numerical Investigation on the Effect of Inflow Mach Numbers on the Combustion Characteristics of a Typical Cavity-Based Supersonic Combustor

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