AIR INLET FOR A TURBOFAN ENGINE

The present invention relates to an air inlet for a nacelle of a jet engine with a front fan, comprising an upper part ( 115 S), a lower part ( 115 I), an inner lateral part ( 115 int) and an outer lateral part (ext), defining a leading edge ( 115 ) between an external wall ( 111 ) of the nacelle an...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser:	CHANEZ PHILIPPE GERARD, LOHEAC PIERRE PHILIPPE MARIE
Format:	Patent
Sprache:	eng
Schlagworte:	AIRCRAFT ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT AVIATION COSMONAUTICS EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLYING SUITS PARACHUTES PERFORMING OPERATIONS TRANSPORTING
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Beschreibung
Zusammenfassung:	The present invention relates to an air inlet for a nacelle of a jet engine with a front fan, comprising an upper part ( 115 S), a lower part ( 115 I), an inner lateral part ( 115 int) and an outer lateral part (ext), defining a leading edge ( 115 ) between an external wall ( 111 ) of the nacelle and an internal wall ( 113 ) forming the air supply channel of the jet engine. According to the invention, the air inlet is characterized in that the leading edge of the outer lateral part ( 115 ext) is to the rear with respect to the leading edge of the inner lateral part ( 115 int). Preferably, the leading edge of the upper part ( 115 S) is likewise to the rear with respect to the leading edge of the lower part ( 115 I).