FIELD: rocket and space technology.
SUBSTANCE: invention can be used in liquid rocket engines (LRE) using metal-comprising rocket fuels. An LRE, one of the fuel components of which is a liquid oxidizer, and the other is a mixture of liquid fuel and powdered metal, with a protective curtain of the nozzle and the internal fire wall of the combustion chamber, which, together with the outer wall of the combustion chamber, forms a cooling path using the oxidizer as a coolant, and with mixing head of the combustion chamber, one of the cavities of which between the fire and middle bottoms is connected to the cooling path of the combustion chamber, and the other cavity between the middle and outer bottoms is connected to the supply system for a mixture of liquid fuel and powdered metal, whereas the combustion chamber is equipped with an additional wall forming, with the outer wall, additional closed cavity connected to the supply system for a mixture of liquid fuel and powdered metal; in the inner and outer walls of the combustion chamber there are coaxial holes in which two-component nozzles are installed, supplying an oxidizer from the cooling path and a mixture of liquid fuel and powdered metal from the additional cavity into the combustion chamber.
EFFECT: improved cooling efficiency of the combustion chamber and liquid-propellant rocket engine nozzle.
1 cl, 2 dwg
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