BLADE FOR A ROTATING BLADED DISK FOR AN AIRCRFT 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...

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Bibliographische Detailangaben
Hauptverfasser:	BASSERY, Josserand Jacques Andre, GARREAU, Edouard Emmanuel, FRANCOIS, Etienne Leon, TSASSIS, Thomas, DESBOIS, Lucas Geoffrey, TANG, Ba-Phuc, TRAHOT, Denis Gabriel, MAXIME, Elsa, JUGE, Samuel Laurent Noel Mathieu
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.