Systematic strategies for thermochemical model reduction in rocket propulsion applications
Standard propulsive applications, such as liquid and hybrid rocket engines, are characterized by highly turbulent purely non-premixed flames. Mixing and combustion of propellants occur under severe thermodynamic conditions, and the numerical characterization of such class of devices is made difficult by the highly non linear thermodynamic and transport properties of the reacting mixture. In this framework, reliable simplified/skeletal chemical kinetic mechanisms and accurate calculation of thermochemical properties, are required for high fidelity simulations.