IMPROVED FIRE RESISTANCE DEVICE DESIGNED TO BE PLACED BETWEEN ONE END OFA 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 (9) of a double-flow aircraft turbomachine and a connecting cowling (30) with which said turbomachine is equipped, the connecting cowling being designed to connect an upstream ring (10), del...

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Bibliographische Detailangaben
Hauptverfasser:	ACHBARI, BAGHDAD, SIMONOTTI, HERVE, JACON, BRUNO ALEXANDRE DIDIER
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 CYLINDERS ENGINEERING ELEMENTS AND UNITS EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLYING SUITS GAS-TURBINE PLANTS GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVEFUNCTIONING OF MACHINES OR INSTALLATIONS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MECHANICAL ENGINEERING PARACHUTES PERFORMING OPERATIONS PISTONS SEALINGS THERMAL INSULATION IN GENERAL 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 (9) of a double-flow aircraft turbomachine and a connecting cowling (30) with which said turbomachine is equipped, the connecting cowling being designed to connect an upstream ring (10), delimiting an inter-flow compartment (8a), to an arm (22) that extends radially across a secondary flow (26) of said turbomachine. According to the invention, the device (50) is produced as a single piece and comprises two contact lips (52a, 52b) which extend along different lines, the first lip (52a) having a C-shaped cross-section. L'invention concerne un dispositif de résistance au feu(50) destiné à être interposé entre unmât d'accrochage (9) d'une turbomachine d'aéronef à double flux et un capotage de raccord (30) équipant cette turbomachine, le capotage de raccord étant destiné à raccorder un anneau amont (10) délimitant un compartiment inter-veine (8a), à un bras (22) traversant radialement une veine secondaire (26) de la turbomachine. Selon l'invention, le dispositif (50) est réalisé monobloc, et comprend deux lèvres de contact (52a, 52b) s'étendant selon des lignes distinctes, dont une première lèvre (52a) de section en C.