Gas turbine engine feather seal arrangement

Details Gas turbine engine feather seal arrangement Gas turbine engine feather seal arrangement

F - Mech Eng,Light,Heat,Weapons

01

D

F01D 11/00 (2006.01)

Patent

CA 2207033

Adjacent platforms (16) have feather seals (34) in complementary slots (22). Hot grooves (40) carry cooling air across the seal and discharge it into the gap (20) between adjacent platforms. Grooves discharging from abutting surfaces are staggered and have a flow component parallel to the axial gas flow through the turbine.

Des plates-formes adjacentes (16) comportent des joints à languette (34) dans des fentes complémentaires (22). Des gorges (40) situées du côté chaud des plates-formes transportent de l'air de refroidissement à travers le joint et le déchargent dans l'espace (20) ménagé entre des plates-formes adjacentes. Les gorges déchargeant l'air à partir de surfaces venant en butée les unes contre les autres sont superposées et présentent un écoulement d'air parallèle à l'écoulement axial de gaz à travers la turbine.

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