CHAMBER OF LIQUID-PROPELLANT ROCKET ENGINE Russian patent published in 2013 - IPC F02K9/42 

FIELD: engines and pumps.

SUBSTANCE: chamber of liquid-propellant rocket engines (LPRE) comprises a regeneratively cooled combustion chamber with critical section and a nozzle, a mixing head comprising a body, a unit of oxidant supply, mostly, oxygen, a unit of main fuel supply, a unit of additional fuel supply, a unit of a flame bottom. In the specified units along concentric circumferences there are coaxial jet nozzles installed, which create central and peripheral areas. The specified coaxial jet nozzles include a hollow tip, which connects the oxidant cavity with the combustion zone, a bushing covering the tip with a gap and connecting the cavity of the first fuel with the combustion zone, at the same time in tips of at least nozzles of the central zone in the outlet part there are radially arranged slots made in the form of alternating ledges and grooves, besides, radially arranged slots are made so that the perimeter of the central part of the jet limited with beam generatrices makes not more than 3s, beam length is 2.3…2.5s, where s - beam thickness, and the number of beams is three. In the bushing, between ledges of the tip, there are channels, the output part of which opens towards the combustion area, the inlet one connects with the cavity of additional fuel, at the same time the outer profile of the specified channels is equidistant to the tip profile.

EFFECT: higher cost-effectiveness of working process when the chamber mixing head operates as three-component, on fuel components of oxygen-kerosene-hydrogen, and also as two-component, on fuel components of oxygen-hydrogen.

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