Computation of the thermoacoustic driving capability of rocket engine flames with detailed chemistry

Computational tools for the prediction of combustion instabilities in rocket engines require a heat release model to represent the flame. In this thesis parameters of such a model are calculated for a hydrogen-oxygen flame using CFD with detailed chemistry. Several excitation methods are considered and their effects on heat release fluctuations are analyzed. Simulations with the thus determined flame transfer function confirm the appearance of thermoacoustic oscillations that were observed in experiments.