| 摘要 |
FIELD: engines and pumps.SUBSTANCE: liquid propellant rocket engine, especially operating on three-component fuel, comprises at least one gas generator, at least one turbopump set, elements of power supply and control, a chamber with 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 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. 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: invention provides for improved completeness of mixture formation when operating on a three-component fuel.5 dwg |
