Abstract
The needle-bolt injector is a convenient method for adjusting the propellant combustion and has attracted a great deal of attention in recent years. However, the effects of injector parameters on the flow and temperature fields in the combustion chamber are rarely investigated. In this study, a new computational fluid dynamic rocket combustor model based on needle-bolt injector is established to study the combustion performance of the gaseous oxygen and gaseous methane (GOx/GCH4) rocket. Three key parameters of needle-bolt injector including the radial fuel injection hole diameter Df, the needle valve diameter Dn and the length of needle into the combustion chamber L are studied. In addition, a special coolant hole for liquid coolant cooling is proposed to reduce the high temperature gathered in thrust chamber. Compared with the chamber wall temperature of 1807 K without cooling, the wall temperature can be reduced to 1467 K after introducing 15% of water coolant. However, with a further increase in coolant ratio from 25% to 30%, the cooling effect is not obvious. The present numerical study can provide important guidance for studying combustion characteristics and cooling performance of rocket combustor with the needle-bolt injector.
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