TURBINE ROTOR DISK WITH INTEGRAL BLADE COOLING AIR SLOTS AND PUMPING VANES

摘要

13DV08619 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.