Turbine rotor disk with integral blade cooling air slots and...

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

Patent

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F01D 5/08 (2006.01) F01D 11/02 (2006.01)

Patent

CA 2059913

13DV08619 ABSTRACT A rotor disk for a gas turbine engine includes a central load-bearing web portion and a centrifugal pump portion located externally of the load-bearing web portion for pumping cooling air into an array of turbine blades. The pump portion includes an enlarged material section formed homogeneously with the web portion and extends axially forwardly and radially inwardly from the rim of the disk.

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