COMPUTER SIMULATION OF THE FUEL COMPONENT MIXING PROCESS IN THE COMBUSTION CHAMBER OF DETONATION ROCKET ENGINE

Abstract

The article is devoted to the problems of mixing fuel components in combustion chambers of detonation rocket engines. Computer simulations are used to evaluate this process effectiveness. The scale of turbulence is determined. The diffusion time in the gas mixture compared with the period of the detonation front transition along the annular combustion chamber. The assumption about the impossibility of a qualitatively mixed mixture obtaining in the described schemes of injector heads is confirmed. This explains the low energy performance of existing models of rotary detonating rocket engines.