FIELD: engines and pumps.
SUBSTANCE: claimed nozzle comprises the case circular element and thrust reverser. Said case circular element can be axially displaced between pulled-in position for engine operation at forward thrust and pulled-out position. Thrust reverser has grates shaped to cylindrical ring sectors aligned with said case element composed by ribs with radial orientation and spaced in axis to make radial guide passages. Case element clears the radial passages through thrust reverser grates at downstream pulled-out position. Radius of ring sectors that makes said grates varies over the case element circumference. Said case circular element comprises inner wall that confines the periphery of cold flow jet and nacelle shell outer wall. Radius of cross-wise cuts of walls between upstream edge of case element and its downstream edge varies at displacement over case element circumference.
EFFECT: decreased vertical size of bypass turbojet.
9 cl, 10 dwg
