Turbine rotor for a gas turbine

Details Turbine rotor for a gas turbine Turbine rotor for a gas turbine

F - Mech Eng,Light,Heat,Weapons

01

D

F01D 5/06 (2006.01)

Patent

CA 2712366

A turbine rotor (1) for a gas turbine with a one-piece compressor housing (11) or a compressor housing (11) which is divided in a first plane, a one-piece turbine housing (12) connected to the compressor housing (11) or a turbine housing (12) which is divided in a second plane different from the first plane comprises a compressor area comprising at least two compressor disks (2.1 - 2.5) and a turbine area comprising at least one turbine disk (13.1, 13.2). The compressor disks and turbine disks are clamped together by a tie rod arrangement having at least one tie rod (6) which has a first fastening area, a second fastening area for clamping at least two compressor disks between the first fastening area and the second fastening area, and a third fastening area for clamping at least one turbine disk.

Rotor (1) de turbine à gaz comportant un carter de compresseur (11) monobloc ou distribué dans un premier plan, un carter de turbine (12) monobloc ou distribué dans un deuxième plan différent du premier plan et accouplé au carter de compresseur (11), ledit rotor comprenant une partie compresseur composée d'au moins deux disques de compresseur (2.1-2.5) et une partie turbine pourvue d'au moins un disque de turbine (13.1-13.2). Les disques de compresseur et de turbine sont étayés par un dispositif de soutien comportant au moins un tirant d'ancrage (6) et présentant une première zone de renforcement, une deuxième zone de renforcement servant à étayer au moins deux disques de compresseur entre la première et la deuxième zone de renforcement, et une troisième zone de renforcement servant à étayer au moins un disque de turbine.

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