TURBINE ENGINE SUCH AS, FOR EXAMPLE, AN AIRPLANE TURBOJET OR TURBOPROP ENGINE

The invention relates to a turbine engine provided with an element (3), comprising a wall (11) and at least one load-bearing member (17) extending substantially perpendicularly relative to the wall (11). Said member (17) is to be attached onto a mounting (18) for attachment onto an aircraft structur...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser:	THIERIET, CÉCILE, BEHAGHEL, LAURENT, DONATIEN, GEYL, STÉPHANE, PERSE, ERWAN, PIERRE, ANTOINE, GUEZEL, YVAN, YOANN
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 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 JOINTS OR FITTINGS FOR PIPES LIGHTING MACHINES OR ENGINES IN GENERAL MEANS FOR THERMAL INSULATION IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES PARACHUTES PERFORMING OPERATIONS PIPES STEAM ENGINES SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING THERMAL INSULATION IN GENERAL TRANSPORTING WEAPONS
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Beschreibung
Zusammenfassung:	The invention relates to a turbine engine provided with an element (3), comprising a wall (11) and at least one load-bearing member (17) extending substantially perpendicularly relative to the wall (11). Said member (17) is to be attached onto a mounting (18) for attachment onto an aircraft structural part, where a thermal protection member (23) surrounds said member (17). Said thermal protection member (23) includes a base flexibly supported on the wall (11) of the element (3). Said base closely fits said wall and at least one covering part that surrounds said load-bearing member. Turbomachine, telle par exemple qu'un turboréacteur ou un turbopropulseur d'avion L'invention concerne une turbomachine équipée d'un élément (3), comportant une paroi (11) et au moins un organe (17) en charge s'étendant sensiblement perpendiculairement à la paroi (11), ledit organe (17) étant destiné à être fixé sur un support (18) servant à la fixation sur une partie structurelle d'un aéronef, où un organe de protection thermique (23) entoure ledit organe (17), ledit organe de protection thermique (23) comprenant une base en appui souple sur la paroi (11) de l'élément (3), ladite base épousant la forme de ladite paroi et au moins une partie de couverture qui entoure ledit organe en charge.