NUMERICAL-SIMULATION OF SUPERSONIC, CHEMICALLY REACTING FLOW USING ANIMPLICIT FINITE-VOLUME METHOD

The thermal design of high-loaded components of combustion chambers re presents a very difficult engineering task. The aerodynamic and therma l analysis procedures currently available to designers do not allow an a priori design without expensive experimental development iterations . Numerical simulations are one possibility for reducing the experimen tal effort. On the one hand, codes exist for the simulation of chemica lly reacting flows; on the other band, few codes exist for the coupled simulation of quid now and heat transfer in solid bodies. A numerical procedure for the calculation of chemically reacting flow with conjug ate heat transfer in the subsonic and supersonic now regime is present ed. The numerical scheme works on the basis of an implicit finite volu me method. The formulation of the governing equations in arbitrary coo rdinates and the use of a multiblock technique even allows the simulat ion of complex geometries. The code is tested using experimental data for the injection of cooling gas into a hot gas stream. The results fo r two different reaction schemes, a one-step global reaction scheme an d a scheme involving 17 elementary reactions and nine species, demonst rate the potential of the method. Furthermore, the code is applied to the injection of hydrogen into an exhaust gas stream with the scope of film cooling with conjugate heat transfer. This approach gives more r ealistic results than the use of adiabatic walls.