Gas turbine engine air intake in a nacelle

The present invention relates to an assembly comprising a gas turbine engine (10) and a nacelle (26) in which the engine is housed, the nacelle including an air intake fairing (26a) that forms an air inlet and includes: a member for deflecting (40) foreign objects, which, together with said fairing,...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser:	YVON DIDIER JEAN-LOUIS, MABBOUX GAETAN JEAN, MINOT PHILIPPE GILLES, VINCENT THOMAS ALAIN CHRISTIAN, CHANEZ PHILIPPE GERARD
Format:	Patent
Sprache:	chi ; eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS
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Beschreibung
Zusammenfassung:	The present invention relates to an assembly comprising a gas turbine engine (10) and a nacelle (26) in which the engine is housed, the nacelle including an air intake fairing (26a) that forms an air inlet and includes: a member for deflecting (40) foreign objects, which, together with said fairing, forms an air intake duct (41); and, downstream from the deflecting member, a secondary deflecting channel (43); and a main (42) channel for supplying air to the engine. Said air intake duct (41) is designed to deflect at least some of the foreign objects sucked in through the air inlet towards the secondary deflecting channel (43). The secondary deflecting channel (43) is shaped such that the flow velocity of the air flowing therethrough increases from upstream to downstream, the secondary channel having an outlet with an opening (43a) leading into the outer wall of the nacelle (26).