Numerical study of the continuous detonation wave rocket engine

Davidenko D. M., GÖKALP İ., Kudryavtsev A. N.

15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2008 (Scopus)

Özet

This paper presents numerical results on the operation of the combustion chamber of a Continuous Detonation Wave Rocket Engine (CDWRE). The propagation of a transversal detonation wave in a layer of continuously injected gaseous mixture H2-O2 has been simulated by a reactive high-resolution Euler code in a 2D approach with periodicity boundary conditions. A parametric study has been conducted to investigate the effect of the injection parameters (injector relative area and injection pressure), combustion chamber length, and spacing between successive detonation fronts on the integral characteristics of the combustion chamber operation. It is found that the detonation wave stably propagates at the Chapman-Jouguet velocity. The spatial period between successive detonations is a geometric scaling factor whereas the injection pressure is a scaling factor for the injection mass flux and the wall pressure. The injection mass flux is the main quantity characterizing the detonation propagation conditions. Copyright © 2008 by CNRS, ITAM.