F - Mech Eng,Light,Heat,Weapons – 01 – D
Patent
F - Mech Eng,Light,Heat,Weapons
01
D
F01D 9/04 (2006.01) F01D 5/03 (2006.01) F01D 5/30 (2006.01) F01D 9/02 (2006.01)
Patent
CA 2622020
A vane assembly (20) of a gas turbine engine (10) comprises a vane that has a vane root (32) connected to an airfoil portion (36) opposite a tip (34) thereof. The vane root includes a platform (46) and a recessed portion (58) interconnecting the platform and the airfoil portion. An elastic grommet (66) comprises a lip portion (84) and a circumferential portion (76) protruding around a perimeter of the lip portion - the lip portion surrounds the recessed portion of the vane. The circumferential portion has a profile that corresponds to that of the airfoil portion and it is engaged between the platform of the vane and the outer surface of a turbine casing (24).
La présente invention a trait à une aube directrice d'entrée (30) comportant un pied (32), une extrémité (34) et une portion de surface portante (36) s'étendant entre le pied et l'extrémité. Une rondelle (66) est utilisée conjointement avec l'aube et présente une lèvre (84) entourant de manière étanche une portion du pied d'aube et une portion périphérique (74) en saillie autour d'un périmètre de la lèvre en engagement avec une surface (48) d'une plate-forme (46) du pied d'aube. La portion périphérique présente un profil identique à celui de la portion de surface portante.
Barnett Barry
Denis David
Norton Rose Or S.e.n.c.r.l. S.r.l./llp
Pratt & Whitney Canada Corp.
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