General Electric Company

Michael James Fedor

David Richard Johns

Scott Jacob Huth

Richard William Johnson

A system for cooling an angelwing coupled to a rotor blade in a gas turbine engine is provided. An angelwing coupled to a shank of a rotor blade includes at least one cooling passage extending from at least one inlet opening coupled in flow communication with a gas turbine engine inner wheelspace to at least one outlet opening coupled in flow communication with a gas turbine engine outer rotor/stator cavity. The at least one outlet opening is located in an upper surface of the angelwing. The at least one cooling passage receives pressurized cooling air channeled from the inner wheelspace, such that the pressurized cooling air is channeled into the at least one inlet opening and discharged from the at least one outlet opening.

Method and system for cooling rotor blade angelwings

Embodiments of the present application include a gas turbine assembly. The gas turbine assembly may include a solid wheel, a turbine aft shaft, and an aft joint connecting the solid wheel to the turbine aft shaft. The turbine assembly also may include a cover plate positioned between the solid wheel and the turbine aft shaft. The cover plate may be configured to direct a flow of compressor extraction fluid inboard through the aft joint and out the turbine aft shaft.

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Simpsonville, SC, United States of America

Michael James Fedor