IMPROVED FIRE RESISTANCE DEVICE DESIGNED TO BE PLACED BETWEEN ONE END OF A MOUNTING STRUT FOR AN AIRCRAFT TURBOMACHINE AND A COWLING OF SAID TURBOMACHINE, DELIMITING AN INTER-FLOW COMPARTMENT

The invention relates to a fire resistance device (50) that is designed to be placed between a mounting strut of a double-flow aircraft turbomachine and a connecting cowling with which said turbomachine is equipped, the connecting cowling being designed to connect an upstream ring, delimiting an int...

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Bibliographische Detailangaben
Hauptverfasser:	JACON, Bruno, SIMONOTTI, Hervé
Format:	Patent
Sprache:	eng ; fre
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS AIRCRAFT ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT AVIATION BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS COSMONAUTICS ENGINE PLANTS IN GENERAL EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLYING SUITS GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES PARACHUTES PERFORMING OPERATIONS STEAM ENGINES TRANSPORTING WEAPONS
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Beschreibung
Zusammenfassung:	The invention relates to a fire resistance device (50) that is designed to be placed between a mounting strut of a double-flow aircraft turbomachine and a connecting cowling with which said turbomachine is equipped, the connecting cowling being designed to connect an upstream ring, delimiting an inter-flow compartment, to an arm that extends radially across a secondary flow of said turbomachine. According to the invention, the device (50) comprises two contacting lips (52a, 52b) which extend along different lines (72a, 72b), a first lip (52a) with a C-shaped section being integrated inside a contact structure (73), and a second lip (52b) having a protruding blocking portion (63) at the end thereof, protecting said contact structure (73). L'invention concerne un dispositif de résistance au feu(50) destiné à être interposéentre unmât d'accrochage d'une turbomachine d'aéronef à double flux et un capotage de raccord équipant cette turbomachine, le capotage de raccord étant destiné à raccorder un anneau amont délimitant un compartiment inter-veine, à un bras traversant radialement une veine secondaire de la turbomachine. Selon l'invention, le dispositif (50)comprend deux lèvres de contact (52a, 52b) s'étendant selon des lignes distinctes(72a, 72b), dont une première lèvre (52a) de section en Cest intégrée au sein d'une structure de contact (73), et une seconde lèvre (52b) comportant à son extrémité une portion d'obstruction en saillie (63) protégeant la structure de contact (73).