关键词: 冲压进气燃烧室;超音速燃烧;三维流;反应动力学;数值仿真

Abstract: A three-dimensional numerical code has been developed to simulate supersonic reacting flows in scramjet combustor. The code employs an implicit, finite volume, Lower-Upper (LU), and time-marching method to solve the complete Navier-Stokes and species equations in a fully coupled and efficient manner. An upwind flux split method named AUSM is adopted to get crisp representations of shock and discontinuities. A global chemistry model is used to simulate the chemical reaction of hydrogen and air. Baldwin-Lomax algebraic turbulence model is used to enclose the governing equations. To testify the reliability of the code, the numerical results are compared with available experimental data.

Key words: Ram air combustor;Supersonic combustion;Three dimensional flow;Reaction kinetics;Numerical simulation