Development of an Eddy Dissipation Model for the use in Numerical Hybrid Rocket Engine Combustion Simulation

Abstract

Within this work, an Eddy Dissipation Model for the combustion process in hybrid rocket engines was developed and implemented into the DLR TAU-Code. The model was developed especially for the propellant combination of hydroxyl-terminated polybutadiene and high concentrated hydrogen peroxide. A numerical generic hybrid rocket combustion chamber was designed to compare the results of the Eddy Dissipation Model simulations with Arrhenius based combustion models. For example, the well validated multistage combustion model from Westbrook and Dryer was applied. The results of the Eddy Dissipation Model simulations are very close to the multistage combustion results and require significantly reduced computing time.