Patent ID: 7331763
Filing Date: 2008-02-19
Classification: F01D,F05D,Y02T

Abstract:
1. A gas turbine section of a gas turbine engine, comprising: (a) a first stage turbine disk including an outer periphery for mounting a plurality of blades thereon and an inner periphery defining a disk hub; (b) a forward outer seal carried on the turbine disk; and (c) a forward shaft cooperating with the first stage turbine disk for transmitting torque generated by the turbine section to a compressor section of the engine, wherein the forward shaft intersects the first stage turbine disk at a non-perpendicular angle in the area of the disk hub for directing sufficient hot air against the disk hub to balance the thermal response rate of the disk hub to the thermal expansion rate of the forward outer seal and wherein the forward shaft extends radially-inwardly from a position axially-forward of the first stage turbine disk to the disk hub.