The invention relates to an injector (3) for a de-icing device for an air intake of an aircraft turbojet nacelle, the injector (3) comprising a peripheral member (30) internally defining a passage duct (6), the peripheral member (30) comprising a peripheral mouth (31) configured to inject a peripheral hot air flow (FAC) so as to circulate a flow of fresh air in the passage duct (6) from upstream to downstream, the peripheral member (30) comprising an inner guide wall (301) located downstream of the peripheral mouth (30), the peripheral member (30) comprising a plurality of members (4) for rotating the hot air flow (FAC) during the injection thereof.
INJECTEUR POUR DISPOSITIF DE DÉGIVRAGE D'UNE ENTRÉE D'AIR D'UNE NACELLE DE TURBORÉACTEUR D'AÉRONEF ET PROCÉDÉ ASSOCIÉ
INJECTOR FOR DE-ICING DEVICE FOR AN AIR INTAKE OF AN AIRCRAFT TURBOJET NACELLE, AND ASSOCIATED METHOD
INJEKTOR FÜR ENTEISUNGSVORRICHTUNG FÜR EINEN LUFTEINLASS EINER FLUGZEUGTURBODÜSENGONDEL UND ZUGEHÖRIGES VERFAHREN
2025-08-13
Patent
Electronic Resource
French
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