FIELD: rocket-space technology.
SUBSTANCE: the method consists in delivery of fuel components through two aligned rotary-type injectors with formation of cylindrical sheets passing into conical ones past the nozzle exit sections of the injectors with a subsequent mixing, ignition and burning in the combustion-chamber volume, the exterior surface of the cone of the inner injector is distant in the direction of the chamber nozzle according to the standards to the exterior surface of the spray cone of the outer injector by the value of the liquid sheet thickness in the nozzle of the outer injector. The sensing point is defined in the zone of completion conical one with rectilinear trajectories of elementary sprays of the exterior injector spray cone obtained at separate spillages of the centrifugal injectors.
EFFECT: enhanced efficiency of mixing of fuel components by way of activation of their liquid-phase and subsequent phases of mixing, enhanced specific thrust pulse of the engine.
3 cl, 9 dwg
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