| 摘要 |
FIELD: engines and pumps.SUBSTANCE: mixing head of a liquid propellant rocket engine comprises 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 main fuel unit with the combustion zone, at the same time in tips of nozzles of the central zone in the outlet part there are radially arranged slots made in the form of alternating ledges and grooves. 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 channels is equidistant to the tip profile.EFFECT: possibility to use a mixing head as a three-component, improved completeness of mixture formation.3 dwg |
