LIQUID PROPELLANT ROCKET ENGINE Russian patent published in 2013 - IPC F02K9/62 F02K9/52 

FIELD: engines and pumps.

SUBSTANCE: liquid propellant rocket engine comprises at least one gas generator, at least one turbopump set, elements of power supply and control, a circular regeneratively cooled chamber with a profiled central body, in the inner cavity of which there are listed units installed, 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. 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, at the same time the number of beams is equal to three, besides, in the bushing, between ledges of the tip, there are channels, the output part of which opens to the combustion zone, and the input one connects with the additional fuel cavity.

EFFECT: improved completeness of mixture formation at all modes operating on a three-component fuel.

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