FIELD: engines and pumps.
SUBSTANCE: method to supply fuel components into a chamber of a three-component liquid propellant rocket engine, preferably, oxygen-kerosene-hydrogen, consists in supply of the specified components into the chamber via coaxial jet nozzles, comprising a hollow tip, which connects an oxidant cavity with a combustion zone, a bushing covering with a gap the tip and connecting the cavity of fuel with the combustion zone, arranged in a mixing head along concentric circumferences and forming central and peripheral areas. At the mode of the first stage oxygen into the cavity of the combustion chamber is supplied via the hollow tip with developed triradial outlet surface of the coaxial jet nozzle, hydrogen - via a profiled gap between the tip and the bushing of the specified nozzle, kerosene - via channels, which are made in the bushing. Besides, the outlet profile of the specified channels is made as equidistant to the tip profile. The outlet part of specified channels opens into the cavity of the combustion chamber, and the inlet one is connected with the cavity of the kerosene unit; at the mode of the second and subsequent stages oxygen into the cavity of the combustion chamber is supplied via the hollow tip with the developed outlet surface of the coaxial jet nozzle, and hydrogen - via the profiled gap between the tip and the bushing of the specified nozzle.
EFFECT: improved completeness of mixture formation.
2 cl, 2 dwg
