The choice of the energy parameters of an oxygen-hydrogen propellant expander cycle rocket engine

In liquid-propellant rocket engines (LRE), made according to an expander cycle scheme, the turbine of the turbopump unit is driven by heated fuel in the cooling path of the combustion chamber (CC). The absence of a gas generator greatly increases the reliability of the rocket engine and provides a number of advantages compared to other engine schemes. At the moment, the existing oxygen-hydrogen liquid-propellant rocket engines by expander cycle scheme do not suit modern tactical and technical requirements for the level of thrust and pressure in the CC of the engine. Therefore, it is necessary to study ways to increase the energy parameters of a liquid-propellant rocket engine and identify promising engine schemes. This article proposes schematic solutions for an oxygen-hydrogen gasless LRE, analyzes the influence of various factors on the specific parameters of the engine, as well as recommendations for designing expander cycle LRE. A mathematical model for calculating the main energy and geometric parameters of the engine has been developed. Prospective pneumohydraulic schemes of an oxygen-hydrogen liquid-propellant expander cyсle rocket engine are proposed, depending on the tactical and technical requirements.