FIELD: rocket technology.
SUBSTANCE: invention relates to rocketry, particularly, to mixing self-igniting fuel components in a combustion chamber of a liquid propellant engine of especially low thrust. Mixing head consists of a mixing chamber with constant cross-section area, with fuel components supply jet nozzles extending into the mixing chamber changing into an expanding to the output antechamber, oxidizer and fuel feed channels to the jet nozzles. According to the invention, the channels to feed oxidizer and fuel before the jet nozzles of fuel components supply intersect between each other. Length of the channels from the point of intersection of the channels to feed oxidizer and fuel till outlet from the mixing chamber does not exceed the length of joint travel of fuel components till the end of the liquid-phase induction period. Cross section of the fuel components supply nozzles is more than the one of the fuel components supply channels. Mixing chamber cross-section area makes 1.5-2.0 of the total area of cross sections of the fuel components supply nozzles.
EFFECT: proposed is a mixing head of a liquid-propellant engine of especially low thrust.
4 cl, 1 dwg
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| MIXING HEAD | 2009 |
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