Abstract:

A three dimensional numerical code has been developed to simulate supersonic reacting flows in scramjet combustor. The code employs a finite volume, lower upper(LU) splitting implicit time marching method to solve the compressible Navier Stokes and species equations in a fully coupled manner. An upwind flux split method named AUSM is adopted. A two step global and an eight step hydrogen air chemistry model are used to simulate the combustion of hydrogen and air. A combustor model with parallel injections has been studied. The pressure, temperature contour as well as the mass fraction distribution of the species are presented. The performance of the two chemistry models are discussed. The eight step model shows superiority to the two step model.

Key words: scramjet, reacting flow, chemistr y model, CFD