FRONT LIP OF A TURBOFAN ENGINE NACELLE COMPRISING HOT-AIR BORES UPSTREAM FROM ACOUSTIC PANELS

The invention relates to a front lip of a turbofan engine nacelle, defined at the rear by a partition wall (6), the lip comprising an annular de-icing space (4) comprising a tube for supplying hot air (40) in order to de-ice the outer walls thereof, said lip also including acoustic panels (42) arran...

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Bibliographische Detailangaben
Hauptverfasser:	BEHAGHEL, PIERRE-FRANÇOIS, DELEHOUZE, ARNAUD, LEMAINS, LAURENCE, VERSAEVEL, MARC
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 INDEXING SCHEME FOR ASPECTS RELATING TONON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES ORJET-PROPULSION PLANTS INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUSSUBCLASSES OF CLASSES F01-F04 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 front lip of a turbofan engine nacelle, defined at the rear by a partition wall (6), the lip comprising an annular de-icing space (4) comprising a tube for supplying hot air (40) in order to de-ice the outer walls thereof, said lip also including acoustic panels (42) arranged on the wall thereof substantially radially facing the axis of the nacelle, characterised in that said front lip comprises hot-air outlet bores (50) which are arranged between the front end of the lip and said acoustic panels (42), which allow a flow of hot air, from said annular space, forming a substantially regular film which covers said acoustic panels with an air boundary layer (52) in order to heat said acoustic panels. Lèvre avant de nacelle de turboréacteur comportant des perçages d'air chaud en amont de panneaux acoustiques Lèvre avant de nacelle de turboréacteur, délimitée à l'arrière par une cloison (6), la lèvre comportant un volume annulaire de dégivrage (4) comportant un tube d'alimentation en air chaud (40) pour effectuer un dégivrage de ses parois extérieures, cette lèvre comprenant de plus des panneaux acoustiques (42) disposés sur sa paroi sensiblement tournée radialement vers l'axe de la nacelle, caractérisée en ce qu'elle comporte des perçages de sortie d'air chaud (50) qui sont disposés entre l'extrémité avant de la lèvre, et lesdits panneaux acoustiques (42), qui permettent un débit d'air chaud, depuis ledit volume annulaire, formant un film sensiblement régulier venant recouvrir par une couche limite d'air (52) lesdits panneaux acoustiques afin de les réchauffer.