초록 ▼

A gas turbine section of a gas turbine engine, including a first stage turbine disk, a forward outer seal carried on the turbine disk and 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. The

A gas turbine section of a gas turbine engine, including a first stage turbine disk, a forward outer seal carried on the turbine disk and 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. 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.

대표청구항 ▼

What is claimed is: 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 forwar

What is claimed is: 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. 2. A gas turbine section according to claim 1, wherein the forward shaft is integrally-formed with the first stage turbine disk. 3. A gas turbine section according to claim 1, wherein the first stage turbine disk includes a forwardly-extending flange positioned radially-outwardly from the forward shaft and radially-inwardly from the blades for supporting an inner peripheral end of the forward outer seal. 4. A gas turbine section according to claim 1, wherein the forward shaft defines a radially-inwardly extending curved surface. 5. A gas turbine section according to claim 4, wherein the forward shaft is integrally-formed with the first stage turbine disk. 6. A gas turbine section according to claim 4, wherein the forward shaft extends radially-inwardly from a position axially-forward of the first stage turbine disk to the disk hub. 7. A gas turbine section according to claim 6, wherein the first stage turbine disk includes a forwardly-extending flange positioned radially-outwardly from the forward shaft and radially-inwardly from the blades for supporting an inner peripheral end of the forward outer seal. 8. A method of balancing the thermal response rate of a turbine disk having a forward shaft, an outer periphery for mounting a plurality of blades and an inner periphery defining a disk hub with the thermal response rate of a forward outer seal mounted to the turbine disk proximate the outer periphery thereof, comprising the steps of: (a) providing the forward shaft with a first predetermined diameter forward of the turbine disk; and (b) providing the forward shaft with a second predetermined diameter at a point of intersection with the turbine disk, the second predetermined diameter being less than the first predetermined diameter for directing sufficient hot air radially inwardly and axially rearwardly towards the disk hub to adjust the thermal expansion of the turbine disk in relation to the thermal expansion of the forward outer seal in order to reduce thermally-induced stress loads on the turbine disk and forward outer seal. 9. A method according to claim 8, wherein the forward shaft defines an inwardly extending arcuate surface. 10. A gas turbine section of a gas turbine engine, comprising: (a) a 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 turbine disk for transmitting torque generated by the turbine section to a compressor section of the engine, the forward shaft having a first predetermined diameter forward of the turbine disk and a second predetermined diameter at a point of intersection with the turbine disk, the second predetermined diameter being less than the first predetermined diameter for directing sufficient hot air radially inwardly and axially rearwardly towards the disk hub to adjust the thermal expansion of the turbine disk in relation to the thermal expansion of the forward outer seal in order to reduce thermally-induced stress loads on the turbine disk and forward outer seal.