Detonation combustion of hydrogen in a convergent-divergent nozzle with a central coaxial cylinder

Abstract

The feasibility of steady detonation combustion of a hydrogen-air mixture entering at a supersonic velocity in an axisymmetric convergent-divergent nozzle with a central coaxial cylinder is considered. The problem of the nozzle starting and the initiation of detonation combustion is numerically solved with account for the interaction of the outflowing gas with the external supersonic flow. The modeling is based on the gasdynamic Euler equations for an axisymmetric flow. The calculations are carried out using the Godunov scheme on a fine fixed grid which allows one to study in detail the interaction of an oblique shock wave formed in the diffuser with the nozzle axis. It is shown that a central coaxial cylinder ensures the starting with the formation of supersonic flow throughout the entire nozzle and stable detonation combustion of a stoichiometric hydrogen-air mixture in the divergent section of the nozzle.

Effects of velocity shear layer on detonation propagation in a supersonic expanding combustor

“…The expansion wave, which has a highpressure gradient, accelerates combustion process by promoting the mixing of unburned and burned gases. Tunik et al 16,17 investigated the detonation combustion of kerosene vapours in an expanding nozzle. They 16,17 observed that with an increase in the Mach number of the incoming flow, the combustion efficiency of kerosene detonation decreases due to the formation of a flow separation zone near the expansion wall.…”

“…Tunik et al 16,17 investigated the detonation combustion of kerosene vapours in an expanding nozzle. They 16,17 observed that with an increase in the Mach number of the incoming flow, the combustion efficiency of kerosene detonation decreases due to the formation of a flow separation zone near the expansion wall. Wang et al 18 reported that the interaction between the oblique detonation wave and expansion fan induces a new wave structure in the expanding channel.…”

Numerical simulation of hydrogen detonative combustion in a convergent-divergent nozzle with a central body

“…Данная работа продолжает исследования по стабилизации детонационного горения водородовоздушных смесей, поступающих в осесимметричные конвергентно-дивергентные сопла с высокой сверхзвуковой скоростью. Ранее в [4][5][6][7][8] численно установлена возможность генерации тяги в результате стабильного детонационного горения водорода в одном и том же сопле на высотах до 16 км при числе Маха набегающего воздушного потока от 7 до 9. На высотах более 20 это сопло не обеспечивает формирование стационарной детонации даже при наличии коаксиального центрального тела «цилиндр-конус».…”