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