Design of the cooling system of a reasuble liquid rocket engine with three-component fuel
Currently, in the field of engine building, the development of three-component propulsion systems (PS) is a very promising task. Liquid-propellant rocket engines (LPRE) operating at the initial stage of launching a launch vehicle (LV) on a vapor of liquid oxygen + kerosene fuel and at high-altitude launch sites using cryogenic fuel (liquid oxygen + liquid hydrogen) are in particular interest. LPRE that use three-component fuel have a high pressure level in the combustion chamber (CC) (up to 30 MPa) and temperatures (up to 4000 K). In this regard, arise questions related to reliable cooling of such engines, as well as ensuring minimal hydraulic fluid losses in the cooling path in order to further use the refrigerant as a working fluid for driving the turbine of a booster turbo pump unit (BTP). The object of research is a two-mode single-chamber three-component liquid-propellant rocket engine, made in a closed circuit with generator gas afterburning. Oxidizing agent - liquid oxygen, fuel - RG-1 kerosene and liquid hydrogen. Cooling of the chamber - combined: it consists of regenerative and internal. The regenerative cooling path is formed by longitudinal milled fins. Supercritical hydrogen is used as the engine coolant. Internal cooling includes a tantalum coating applied to the fire wall of the chamber in the critical section. The article examines the problems of organizing the cooling system (CO) and the implementation of effective heat removal from the firing wall of a three-component rocket engine. Basing on the existing liquid-propellant engine cooling systems, optimal circuit solutions and measures are proposed in the RESEARCH to remove the thermal load in the most stressed places. A mathematical model has been developed for calculating the CO of a three-component LPRE. The results of the design calculation of cooling using several calculation methods are presented.