FIELD: rocket equipment.
SUBSTANCE: oxygen-kerosene liquid-propellant rocket engines (LRE) of a closed circuit. A method for removing kerosene during LRE shutdown from the internal cavities of the chamber: the cooling path, from the kerosene supply cavity, a curtain for cooling the wall from the thermal effects of combustion products, based on the displacement of kerosene when the engine is stopped with water, providing for the displacement of fuel from the internal cavities of the chamber and excluding kerosene residues, filling the internal cavities with water and closing from the penetration of oxygen, and in the process of shutdown, water is introduced from an additional tank installed on the kerosene supply line with the kerosene supply turned off. A liquid-propellant rocket engine with a turbopump system for supplying propellant components and a valve system contains an additional tank filled with water and having a displacement system for supplying water to the fuel pipeline, a valve at the outlet of the tank that shuts off the flow of water into the fuel pipeline during engine operation and opens when the engine is shut down to supply water instead of kerosene, while the additional tank has two cavities separated by a membrane so that one cavity is connected through a valve to the kerosene supply pipeline, and the other, gas, is connected to the high pressure line of the engine through a valve.
EFFECT: decrease in the aftereffect pulse from the combustion of fuel residues due to the exclusion of liquid or evaporated fuel entering the chamber and elimination of the interaction of the explosive nature of fuel component residues when gaseous oxygen penetrates into the internal cavities of the chamber, previously filled with kerosene.
8 cl, 1 dwg
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Authors
Dates
2023-09-29—Published
2022-11-03—Filed