Research of the effect of an extended-surface of the chamber cooling jacket on the performance parameters of an oxygen-hydrogen liquid-propellant rocket engine by expander cycle

Liquid propellant rocket engines by expander cycle are used for the upper stages of launch vehicles and upper stages. Their main feature is the absence of a gas generator, and the turbine of the turbopump unit is driven by fuel heated in the cooling jacket of the combustion chamber. This scheme design of the engine increases its reliability and ensures a high level of specific impulse of the engine. However, modern oxygen-hydrogen liquid propellant rocket engines by expander do not always respond the growing requirements of specific engine parameters, in particular, pressure in the combustion chamber and specific impulse. Determining the optimal values of these engine parameters of such a scheme depends on optimizing energy balance, intensifying heat transfer in the cooling jacket, and effective heat exchange from the construction of chamber. This article proposes a method for intensification of the heat transfer in the cooling jacket due to the developed surface of heat exchange in the cooling jacket by using additional ribs of the firing wall of the combustion chamber. According to the developed mathematical model for calculating the energy and geometric parameters of the engine, extremes in the intensification of heat transfer and the specific impulse of the engine were identified depending on the pressure in the combustion chamber and the energy characteristics of the turbopump unit.
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