NUMERICAL-ANALYSIS OF 2-RING FLAME STABILIZER FLOWS IN AIRCRAFT AFTERBURNERS

A computational procedure is described for the calculation of isotherm al flow fields of two-ring flame stabilizers in practical afterburners and also for the reacting flow parameters in a research afterburner. The predictions have been obtained using a finite volume solution proc edure for the steady three-dimensional elliptic equations of fluid flo w. The physical models include the k-epsilon turbulence model, eddy br eakup model, two-step reaction model, droplet vaporization and combust ion model, and six-flux radiation model. The presence of radial gutter s and staggering the distance between two-ring gutters alter the after burner flow patterns considerably, including the elimination of diffus er stall and flow separation losses near the diffuser. The predicted a nd measured emissions in the research afterburner geometry agree quali tatively. The effect of the fuel to air ratio and location of the fuel injector on the temperature and species concentration distribution ar e presented in detail.