DOUBLE-FLOW TURBOJET ENGINE WITH BIROTATIVE FAN Russian patent published in 2007 - IPC F02K3/72 

FIELD: mechanical engineering; turbojet engines.

SUBSTANCE: proposed double-flow turbojet engine contains birotative fan arranged in channel of outer loop and limited from outer side by engine nacelle, and gas generator and reversing device with deflecting cascades. Nozzle with axially movable casing is installed at outlet of channel of outer loop. Fairing of engine gas generator is provided with hinged flap connected with operating mechanism. Ratio of outer diameter of nozzle at outlet of channel of outer loop to outer diameter of birotative fan at leading edge of first blade in direction of air flow is 1-1.5. Ratio of minimum diameter of fairing of gas generator at nozzle exit to maximum outer diameter of fairing of gas generator at nozzle exit is 1.05-1.3. Ratio of passage area of deflecting cascades of reversing device to passage area of holes in flaps and between flaps of gas generator fairing at reverse thrust mode is 3 to 10.

EFFECT: increased economy, improved reliability, reduced weight of double-flow turbojet engine owing to increase of tradeoff thrust and reduction of hydraulic losses by decreasing outer diameter of birotative fan, adjusting of passage area of nozzle and reducing curvature of outer surface of engine micelle.

3 dwg