Patent ID: 7578656

Claim:
A gas turbine engine, comprising a high pressure turbine section, including a gas turbine engine disk defining a disk hub surface having an annular cylindrical surface section and a radially-displaced annular hub surface section comprising an axially-extending and radially-displaced chamfer for disrupting an axial path from the disk hub to the disk hub surface, the chamfer formed in a forward side of the disk hub and extending forwardly from the annular cylindrical surface section at a position below and in vertical alignment with a geometrically-centered, lowest internal temperature portion of the disk hub, the annular cylindrical surface section extending axially to a rearward side of a rearward shaft for shifting the lowest internal temperature portion and the maximum axial stress out of vertical alignment with the geometrically-centered portion of the disk hub, thereby reducing the magnitude of the axial stress on the disk hub.