Classification of injection systems of a rotational detonation rocket engine

Abstract

The article deals with the problems of mixing fuel components in combustion chambers for detonation rocket engines. The main idea that pushes scientists to search in this direction is the higher thermodynamic efficiency of detonation compared to conventional combustion at subsonic velocities. In addition, the detonation process can occur at relatively low pressure components of the fuel components, which allows abandoning heavy power systems and using a simple squeeze-roller feed system. Well-known experimental studies are used to further research ways to solve problems with blending.
The purpose of the work is computer flow simulation of hydrogen and air mixture in the combustion chamber near the nozzle head of a rotary detonation engine.
Computer simulation is used to evaluate the process efficiency of the fuel components mixing. Five variants of nozzle heads schemes are considered. Modeling of air and hydrogen flow in different nozzle head schemes is carried out. The turbulence scale for each scheme of the nozzle head is determined. The classification of circuits according to turbulence scale is conducted. It is shown that the classification corresponds decreasing of engine efficiency too. It is suggested to use antechamber with pre-mixing fuel components in one volume and detonation their mixture in another.