Disk of a disk rotor for a gas turbine

F - Mech Eng,Light,Heat,Weapons – 01 – D

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F01D 5/06 (2006.01)

Patent

CA 2551287

Disk of a disk rotor for a gas turbine comprising a central portion (22), an intermediate portion (24), an outer portion (28), a series of axial pass- through holes (27) for a series of tie rods and a series of slots (50) for housing a corresponding series of vanes, the central portion (22) comprises a central axial pass-through hole (23), a first collar (30) situated at a first end and a second collar (40) situated at a second end of the central portion (22). The series of holes (27) is positioned in the outer portion (28) of the disk so as to obtain high dynamic characteristics of the rotor and at the same time a sufficient useful life thereof.

L'invention concerne un disque de rotor à disque pour turbine à gaz comprenant une partie centrale (22), une partie intermédiaire (24), une partie extérieure (28), une série de trous axiaux traversants (27) pour une série de tiges de raccordement ainsi qu'une série de fentes (50) destinées à loger une série correspondante d'ailettes, la partie centrale (22) comprend un trou traversant central axial (23), un premier collier (30) situé au niveau d'une première extrémité et un second collier (40) situé au niveau d'une seconde extrémité de la partie centrale (22). La série de trous (27) est positionnée dans la partie extérieure (28) du disque, de manière à obtenir des caractéristiques dynamiques élevées du rotor et en même temps une vie utile suffisante pour celui-ci.

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