BLADE FOR A BLADED ROTOR DISK OF AN AIRCRAFT TURBOMACHINE, CORRESPONDING BLADED ROTOR DISK, TURBINE AND TURBOMACHINE

To increase the inertia of a sealing lip of a blade for an aircraft turbine engine, and thus improve the service life of such a sealing lip, the sealing lip is conformed so as to have a trough in the outer surface thereof and a corresponding boss in the inner surface thereof, the trough and the boss...

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Bibliographische Detailangaben
Hauptverfasser: DESBOIS, Lucas, Geoffrey, GARREAU, Edouard, Emmanuel, TSASSIS, Thomas, JUGE, Samuel, Laurent, Noël, Mathieu, FRANCOIS, Etienne, Léon, TANG, Ba-Phuc, MAXIME, Elsa, TRAHOT, Denis, Gabriel, BASSERY, Josserand, Jacques, André
Format: Patent
Sprache:eng ; fre ; ger
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Zusammenfassung:To increase the inertia of a sealing lip of a blade for an aircraft turbine engine, and thus improve the service life of such a sealing lip, the sealing lip is conformed so as to have a trough in the outer surface thereof and a corresponding boss in the inner surface thereof, the trough and the boss being defined based on a connection cross section of the sealing lip to a blade body, and being formed at a distance from a free axial end of the sealing lip.