Numerical Modeling of the Rotating Detonation in an Annular Combustion Chamber Fed with Hydrogen-Oxygen Mixture

Numerical simulations of a transverse detonation wave continuously rotating in an annular cylindrical combustion chamber are performed. The investigation is aimed at a better understanding of the processes in the continuously operating detonation wave rocket engine fed with stoichiometric hydrogen-oxygen mixture. The two-dimensional Euler equations for chemically reacting flow are solved using a high-order weighted essentially non-oscillatory scheme coupled with a semi-implicit Runge-Kutta time integration method. Finite-rate chemistry is described by a kinetic model including 6 species and 7 reversible reactions. The flow structure in the combustion chamber is investigated and the dependence of main flow characteristics and combustion chamber performance on the injection total pressure, chamber length and azimuthal period is studied.