INLET CONE FOR AN AIRCRAFT TURBINE ENGINE AND ASSOCIATED AIRCRAFT TURBINE ENGINE

The present invention concerns an inlet cone (10) for an aircraft turbine engine (1), comprising a frustoconical body (12) and a tip (11) made from elastically deformable material attached to an end (12p) of smaller diameter of the body (12), the tip (11) comprising an apex configured to be situated...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser: BATONNET BAPTISTE, LOUIS ALBAN
Format: Patent
Sprache:chi ; eng
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