FIELD: engines and pumps.
SUBSTANCE: turbojet engine afterburner combustion chamber combustion zone stabilization method includes colliding with each other paired fuel-air jets radial supply into the incident flow. Each pair of colliding jets axes are located in the passing through the engine axis plane. Each pair axes are inclined towards each other. Angle between the axes is 45–120 degrees.
EFFECT: invention is aimed at increase in the afterburner combustion chamber reliability, hydraulic losses and the infrared radiation level reduction.
3 cl, 4 dwg
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