Mixing augmentation of transverse injection in scramjet combustor

A method for augmenting the mixing of transverse injection in a scrainjet combustor is suggested, and its effectiveness is checked by numerical methods. The intent was to promote streamwise vorticity by modifying the injector geometry using a cavity to increase the mixing rate and penetration. A three-dimensional Navier-Stokes code adopting the upwind method of Edwards's low diffusion flux splitting scheme was used. The kappa-omega SST turbulence model was used to calculate the turbulent viscosity. The injector models proposed showed remarkable increases of streamwise vorticity and, as a result, significant improvements in mixing characteristics such as mixing rate and penetration. However, the proposed models also showed additional losses of stagnation pressure. The mixing characteristics are strongly related to the jet-to-cross How momentum flux ratio J. In the case of higher values of J, slower mixing rates, higher penetration, and more losses of stagnation pressure are shown.