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A gas turbine engine includes an axial high pressure compressor includes a rear hub disposed aft of an aft rotor segment. The rear hub includes an inner surface, an outer surface, and a sealing face, wherein the sealing face is sealingly engaged with the aft rotor segment, and in fluid communication

A gas turbine engine includes an axial high pressure compressor includes a rear hub disposed aft of an aft rotor segment. The rear hub includes an inner surface, an outer surface, and a sealing face, wherein the sealing face is sealingly engaged with the aft rotor segment, and in fluid communication with the cooling channel. The cooling channels are configured to delivery air to contact the inner surface of the rear hub.

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1. A gas turbine engine compressor comprising: an aft rotor segment comprising an outer rim, an inner rim, and a cooling channel disposed between the inner rim and the outer rim; anda rear hub disposed aft of the aft rotor segment and comprising an inner surface, an outer surface, and a sealing face

1. A gas turbine engine compressor comprising: an aft rotor segment comprising an outer rim, an inner rim, and a cooling channel disposed between the inner rim and the outer rim; anda rear hub disposed aft of the aft rotor segment and comprising an inner surface, an outer surface, and a sealing face, wherein the sealing face is sealingly engaged with the aft rotor segment, wherein the inner surface of the rear hub is in fluid communication with the cooling channel and wherein a portion of the outer rim extends aft of the sealing face of the rear hub. 2. The gas turbine engine compressor of claim 1, wherein the sealing face of the rear hub is sealingly engaged with the outer rim of the aft rotor segment. 3. The gas turbine engine compressor of claim 1, wherein the cooling channel is configured to delivery air to contact the inner surface of the rear hub. 4. The gas turbine engine compressor of claim 1, wherein the rear hub further comprises a low pressure sink and a cooling path, wherein the cooling path directs air from the cooling channel to the low pressure sink. 5. The gas turbine engine compressor of claim 1, wherein an outer radius of the sealing face is equal to or less than a radius of the outer rim. 6. The gas turbine engine compressor of claim 1, wherein the sealing face comprises a hub inlet port that aligns and is in fluid communication with the cooling channel. 7. The gas turbine engine compressor of claim 1, wherein the aft rotor segment comprises a plurality of cooling channels. 8. The gas turbine engine compressor of claim 7, wherein the sealing face comprises the same number of hub inlet ports as cooling channels, and each hub inlet port is in fluid communication with a corresponding cooling channel. 9. The gas turbine engine compressor of claim 1, wherein the sealing face engages with the inner rim. 10. A gas turbine engine comprising: an axial high pressure compressor comprising a rotary assembly, wherein the rotary assembly comprises an aft rotor segment comprising an outer rim, an inner rim, and a cooling channel disposed between the inner rim and the outer rim, anda rear hub disposed aft of the aft rotor segment and comprising an inner surface, an outer surface, and a sealing face, wherein the sealing face is sealingly engaged with the aft rotor segment, wherein the inner surface of the rear hub is in fluid communication with the cooling channel wherein the aft rotor segment comprises a plurality of cooling channels and wherein the sealing face comprises the same number of hub inlet ports as cooling channels and each hub inlet port is in fluid communication with a corresponding cooling channel. 11. The gas turbine engine of claim 10, wherein the sealing face of the rear hub is sealingly engaged with the outer rim of the aft rotor segment. 12. The gas turbine engine of claim 10, wherein the cooling channel is configured to delivery air to contact the inner surface of the rear hub. 13. The gas turbine engine of claim 10, wherein the rear hub further comprises a low pressure sink and a cooling path, wherein the cooling path directs air from the cooling channel to the low pressure sink. 14. The gas turbine engine of claim 10, wherein an outer radius of the sealing face is equal to or less than a radius of the outer rim. 15. The gas turbine engine of claim 10, wherein the sealing face comprises a hub inlet port that aligns and is in fluid communication with the cooling channel. 16. The gas turbine engine of claim 10, wherein the sealing face engages with the inner rim. 17. The gas turbine engine of claim 10, wherein a portion of the outer rim extends aft of the sealing face of the rear hub.