ROTATING INLET COWL FOR A TURBINE ENGINE, INCLUDING AN ECCENTRIC FRONT END

The present invention relates to a rotating inlet cowl (30) for a turbine engine, having a rotational axis (34) and the front end of which is eccentric to said rotational axis (34). Further, a front cone (32) of the cowl is truncated by a truncating surface (70) that defines the front end (44) of th...

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Bibliographische Detailangaben
Hauptverfasser:	DELAPIERRE, MICKAEL, WINTENBERGER, SYLVIE, GIGNOUX, HERVE, LORO, GAEL
Format:	Patent
Sprache:	eng ; fre
Schlagworte:	AEROPLANES 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 EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLYING SUITS GAS-TURBINE PLANTS HEATING HELICOPTERS 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 present invention relates to a rotating inlet cowl (30) for a turbine engine, having a rotational axis (34) and the front end of which is eccentric to said rotational axis (34). Further, a front cone (32) of the cowl is truncated by a truncating surface (70) that defines the front end (44) of the inlet cowl. La présente invention se rapporte à un capot d'entrée tournant (30) pour turbomachine, présentant un axe de rotation (34) et dont l'extrémité avant (44) est agencée de manière excentrée par rapport à cet axe de rotation (34). De plus, un cône avant (32) du capot est tronqué par une surface de troncature (70) définissant l'extrémité avant (44) du capot d'entrée.