Numerical Modeling of Continuous Detonation in NonStoichiometric Hydrogen–Oxygen Mixtures
S. A. Zhdan, A. S. Syryamin
Keywords: continuous spin detonation, combustor, hydrogen–oxygen mixtures, transverse detonation waves, flow structure, mathematical modeling, specific impulse
Abstract
A twodimensional unsteady gasdynamic mathematical model of continuous spin detonation in a nonstoichiometric hydrogen–oxygen mixture in an annular combustor of a rockettype engine is formulated. An analysis of the governing parameters shows that this model is an eigenvalue problem, where the eigenvalue is the problem period, which cannot be arbitrarily prescribed, but which has to be sought in the course of solving the problem. Numerical modeling of the dynamics of transverse detonation waves is used to elucidate the influence of the fueltooxidizer equivalence ratio on the wave structure and specific impulse, and the eigenvalue (minimum period of the problem) is determined as a function of the specific flow rate of the mixture. These eigenvalues are demonstrated to agree with experimental data. In the case of continuous spin detonation, addition of an expanding nozzle to a constantsection channel is shown to increase the specific impulse.
