Multi-component bladed rotor for a turbomachine

Details Multi-component bladed rotor for a turbomachine Multi-component bladed rotor for a turbomachine

F - Mech Eng,Light,Heat,Weapons

01

D

F01D 5/06 (2006.01) F01D 5/30 (2006.01)

Patent

CA 2709167

A multipart bladed rotor (1) for a flow machine, particularly a gas turbine or steam turbine or an axial compressor, has at least two disks (2) whose front sides, which face one another, are connected to one another, particularly by positive engagement, in a separating plane (7) so as to be fixed with respect to rotation relative to one another, wherein a groove (10) for receiving a blade root (14) of at least one rotor blade is formed in the separating plane.

L'invention concerne un rotor à aubes (1), en plusieurs parties, pour une turbomachine, notamment une turbine à gaz ou à vapeur ou bien un compresseur axial. Ce rotor comporte au moins deux disques (2) dont les faces frontales orientées l'une vers l'autre sont reliées solidaires en rotation, notamment par coopération de formes, dans un plan de joint (7), une gorge (10) étant ménagée dans ce plan de joint pour recevoir le pied (14) d'au moins une aube mobile.

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