Abstract: A compressor for a turbine engine includes multiple compressor disks having rotor blades mounted about the circumference of each of the disks. A plurality of stator blades extend between the rotor blades of axially adjacent disks. A knife edge seal is supported and retained by retaining flanges extending from a rim on each disk, and contacts the stator blades to limit the recirculation of air within the compressor. A plurality of lock assemblies are spaced about the circumference of disk backbones formed in each disk, with a plurality of knife edge seals located between each lock assembly. When in the lock position the lock assemblies reduce the slack used for assembly of the final knife edge seal to prevent shifting and rotating during operation.

Abstract: A compressor for a turbine engine includes multiple compressor disks having rotor blades mounted about the circumference of each of the disks. A plurality of stator vanes extend between the rotor blades of axially adjacent disks. A knife edge seal segment is supported by each disk backbone extending from the disks and contacts the stator vanes to restrict leakage of compressed air from between the stator vane and the compressor rotor to limit the recirculation of air. Retaining flanges extend from each disk rim to retain the knife edge seal segments to the disk backbone and spacer bridges integral to the knife edge seal segments prevent axial movement of the knife edge seal segments. A plurality of lock assemblies are spaced about the circumference of the disk backbone to prevent circumferential shifting and rotating of the knife edge seal segments during operation.

Abstract: A compressor for a turbine engine includes multiple compressor disks having rotor blades mounted about the circumference of each of the disks. A plurality of stator blades extend between the rotor blades of axially adjacent disks. A knife edge seal is supported and retained by retaining flanges extending from a rim on each disk, and contacts the stator blades to limit the recirculation of air within the compressor. A plurality of lock assemblies are spaced about the circumference of disk backbones formed in each disk, with a plurality of knife edge seals located between each lock assembly. When in the lock position the lock assemblies reduce the slack used for assembly of the final knife edge seal to prevent shifting and rotating during operation.

Abstract: A compressor for a turbine engine includes multiple compressor disks having rotor blades mounted about the circumference of each of the disks. A plurality of stator vanes extend between the rotor blades of axially adjacent disks. A knife edge seal segment is supported by each disk backbone extending from the disks and contacts the stator vanes to restrict leakage of compressed air from between the stator vane and the compressor rotor to limit the recirculation of air. Retaining flanges extend from each disk rim to retain the knife edge seal segments to the disk backbone and spacer bridges integral to the knife edge seal segments prevent axial movement of the knife edge seal segments. A plurality of lock assemblies are spaced about the circumference of the disk backbone to prevent circumferential shifting and rotating of the knife edge seal segments during operation.