Ejection nozzle for turbojet with integrated thrust reverser

The propulsion nozzle has an ejection channel (7) in an outer housing (9) with hot (14) and cold (16) shutters and a thrust reversal system (30) with two identical flaps (31, 32) that pivot at the rear end of the ejection channel on either side of its axis of symmetry (12). The nozzle incorporates a...

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Bibliographische Detailangaben
Hauptverfasser:	CHARIER, GILLES ALAIN, ROLLIN, GILLES LOUIS, GUYONNET, XAVIER JEAN-MICHEL ANDRE
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AEROPLANES AIRCRAFT AVIATION BLASTING COMBUSTION ENGINES COSMONAUTICS HEATING HELICOPTERS HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MECHANICAL ENGINEERING PERFORMING OPERATIONS TRANSPORTING WEAPONS
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Beschreibung
Zusammenfassung:	The propulsion nozzle has an ejection channel (7) in an outer housing (9) with hot (14) and cold (16) shutters and a thrust reversal system (30) with two identical flaps (31, 32) that pivot at the rear end of the ejection channel on either side of its axis of symmetry (12). The nozzle incorporates a system for moving the flaps apart during take-off, in the form of a power cylinder (50) between supporting arms (33, 34), and the cold shutters are designed to ensure an obstacle-free aerodynamic profile with the flaps in take-off and cruising configurations.