Simplified Numerical Modeling of Film Cooling and Mixture Ratio Bias in Liquid Rocket Thrust Chambers

High performance liquid rocket engines are characterized by high pressure and high wall heat fluxes which have to be inevitably managed by an active cooling system. The most commonly used is the regenerative cooling system, which, however, may result insufficient. In such cases, cooling capabilities can be enhanced by other active cooling means, like film cooling or mixture ratio bias of peripheral injectors. The additional active cooling system has a cost in terms of performance. The present numerical parametric study provides a general cost-benefit analysis of this cooling systems in an oxygen-methane engine.