Patent ID: 7470113

Claim:
A compressor for a jet engine comprising: a plurality of disks each defining a disk rim having a disk backbone; a plurality of knife edge seal segments located about the circumference of each of the backbones, wherein each of the plurality of knife edge seal segments are supported by the backbones and retained to the disk rims; and wherein each disk rim comprises a retaining flange protruding from the disk rim and each of the plurality of knife edge seal segments are supported by and retained by the retaining flanges; a first backbone protruding in a first direction, a second backbone protruding in a second direction, opposing the first direction, and a portion of the plurality of knife edge seal segments are supported by the first backbone, and the remaining knife edge seal segments are supported by the second backbone; a plurality of lock assemblies spaced about the circumference of the disk backbones to retain at least one of the plurality of knife edge seal segments to prevent circumferential movement of the plurality of knife edge seal segments about the plurality of disks; and a spacer bridge extending from each of the plurality of knife edge seal segments and located between each of the plurality of lock assemblies, wherein a first plurality of spacer bridges are supported by the first backbone and a second plurality of spacer bridges are supported by the second backbone, and the first plurality of spacer bridges are each in contact with at least one of the second plurality of spacer bridges.