ASSEMBLY, GAS TURBINE COMPRESSOR ROTOR AND PROCESS FOR SEALING A GAS TURBINE ENGINE COMPRESSOR ROTOR ASSEMBLY

A double ring axial seal (50) for a disk (30) and blade (34) is provided. The disk (30) includes an array of blade slots (32) at a perimeter (31) of the disk (30) configured to receive a root portion (36) of the blade (34). The blade (34) includes a platform (38) located between the root portion (36) and an airfoil (40) extending from the platform (38) opposite the root portion (36). The platform (38) includes a receiver (56) with an overhang (74) proximate the root portion (36). The platform (38) including a hook (60) opposite the receiver (56) proximate the root portion (36). A disk slot (48) is formed on a first side of the disk (30) proximate the array of blade slots (32). A first axial seal ring (54) is coupled with the disk slot (48) and the receiver (56). The first axial seal ring (54) has a cutout (70) proximate an outer perimeter (72) of the first axial seal ring (54). The cutout (70) is sized to receive the overhang (74) of the blade platform (38). The receiver (56) has a contour (64) configured to redirect the first axial seal ring (54) axially toward the blade (34) and disk (30) for axial sealing. A second axial seal ring (58) is inserted into the hook (60) of the blade platform (38) proximate the array of blade slots (32) adjacent a disk face (62) on a side of the disk (30) opposite the first axial seal ring (54). A gas turbine engine compressor rotor is also provided. A process for sealing a gas turbine engine compressor rotor assembly is also provided.