Seal for a turbojet engine pylon and nacelle, and turbojet engine pylon-nacelle assembly incorporating such a seal

The fireproof seal is intended for an assembly comprising a turbojet engine pylon and nacelle, in particular an O-duct type. The nacelle comprises a fixed internal nacelle structure (4) and a primary exhaust nozzle (5) for combustion gas, which can be driven at least partially in a relative longitud...

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Bibliographische Detailangaben
Hauptverfasser:	BEILLIARD STEPHANE, PHI ALEXANDRE, GUILLON JEAN-BERNARD
Format:	Patent
Sprache:	chi ; eng
Schlagworte:	AIRCRAFT ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT AVIATION BLASTING COMBUSTION ENGINES COSMONAUTICS EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLYING SUITS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MECHANICAL ENGINEERING PARACHUTES PERFORMING OPERATIONS TRANSPORTING WEAPONS
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Beschreibung
Zusammenfassung:	The fireproof seal is intended for an assembly comprising a turbojet engine pylon and nacelle, in particular an O-duct type. The nacelle comprises a fixed internal nacelle structure (4) and a primary exhaust nozzle (5) for combustion gas, which can be driven at least partially in a relative longitudinal linear movement in the direction of the longitudinal axis of the nacelle (A). The seal comprises a plurality of baffles (10-15) arranged longitudinally such as not to interfere during a longitudinal linear movement (B) between the primary combustion gas exhaust nozzle and the fixed internal nacelle structure.