Method and apparatus for supplying cooling air to turbine rotors

摘要

A gas turbine engine rotor assembly includes a plurality of aerodynamic devices (66) to direct airflow radially inward. The gas turbine engine rotor assembly includes a rotor shaft (44) that includes a plurality of openings (52). The aerodynamic devices include a pair of vane segments (140) and a pair of sidewalls (142). A contoured outer surface (132) includes an opening (74) and permits the aerodynamic device to be positioned against an inner surface (50) of the rotor shaft, and a flange ring (60, 64) defines a pocket (65). The aerodynamic device fits within the pocket to concentrically align the openings (52,74).