Blade for a rotating bladed disk for an aircraft turbine engine comprising a sealing lip having an optimized non-constant cross section

Blade for a rotating bladed disk for an aircraft turbine engine comprising a sealing lip having an optimized non-constant cross section

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...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser: Francois, Etienne Leon, Garreau, Edouard Emmanuel, Bassery, Josserand Jacques Andre, Maxime, Elsa, Tang, Ba-Phuc, Desbois, Lucas Geoffrey, Juge, Samuel Laurent Noel Mathieu, Trahot, Denis Gabriel, Tsassis, Thomas
Format: Patent
Sprache:eng
Schlagworte:
BLASTING
ENGINE PLANTS IN GENERAL
HEATING
LIGHTING
MACHINES OR ENGINES IN GENERAL
MECHANICAL ENGINEERING
NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES
STEAM ENGINES
WEAPONS
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Beschreibung
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.