GAS TURBINE ENGINE ROTOR DISK-SEAL ARRANGEMENT

摘要

A disk-seal arrangement for a gas turbine engine rotor includes a blade retention disk having a longitudinally opening slot therein and a seal disk juxtaposed to said blade retention disk and a single anti-rotation tab received within the blade retention disk slot. The seal disk also includes a pair of balance slots disposed immediately adjacent the antirotation tab to offset the weight thereof for preserving rotor balance. A split ring is disposed longitudinally between the blade retention and seal disks for reacting longitudinal loading therebetween. The ends of the split ring seat against side surfaces of the antirotation between the split ring and the blade retention and seal disks.

主权项

1. A disk-seal arrangement for a gas turbine engine rotor having a longitudinal axis of rotation, comprising:
a blade retention disk having a longitudinally opening antirotation slot therein; a seal disk juxtaposed to said blade retention disk, said seal disk including a single antirotation tab having a pair of side surfaces and received in said antirotation slot in said blade retention disk said seal disk further including a pair of balance slots disposed immediately adjacent said side surfaces of said antirotation tab; and a generally annular split ring having a pair of ends and being disposed longitudinally between and engageable with said blade retention disk and said seal disk for reacting longitudinal loading therebetween, said ends of said split ring being seated against said side surfaces of said antirotation tab.