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Abstract

A method and apparatus for reducing thermal distress and creep of a disk post in a gas turbine engine, the disk post being defined between an adjacent pair of blade roots of a respective pair of turbine blades in a turbine disk. The blade roots extend radially outward of the turbine disk and each terminate in a blade platform to form a cavity above the disk post. A seal generally covers the cavity for preventing a flow of combustion gases over the disk post. The seal includes axial segments defining a channel over a radially outer surface of the disk post. A flow of insulative air is directed into the channel defined over the disk post and diffused to reduce its velocity. The insulative air effectively reduces heat transferred from the blade platforms and combustion gases to the disk post.

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First Claim