Abstract: An air separator for a turbine engine is provided. The air separator includes an aft air separator member (10) having an annular frame (14) which defines a chamber (16) configured to engage disc shoulders (18) configured in a first stage of the turbine engine. The aft air separator member (10) is constrained from movement along a radial direction by the disc shoulders engaged in the chamber of the aft air separator member. A forward air separator member (12) is affixed at a forward end thereof to a torque tube (20) to constrain movement along the radial direction. The forward air separator includes at an aft end thereof a flange (22) that engages the aft air separator member. The forward air separator member is constrained from outward radial movement along the radial direction by way of a recess (24) constructed in a portion of the aft air separator member.

Abstract: A sealing band is located in opposing sealing band receiving slots of adjacent turbine disks to seal an annular gap therebetween. A through hole is defined in one of the disks, wherein the through hole defines a longitudinal hole axis and extends to the sealing band receiving slot in the disk. At least one engagement feature is defined on the disk and extends laterally of the through hole, perpendicular to the longitudinal hole axis. A pin member extends through the hole and is positioned within the sealing band receiving slot passing through an opening in the sealing band for resisting movement of the sealing band relative to the disk. The pin member includes a laterally extending cooperating feature positioned in engagement with the engagement feature for retaining the pin within the opening in the sealing band.

Abstract: An air separator for a turbine engine is provided. The air separator includes an aft air separator member (10) having an annular frame (14) which defines a chamber (16) configured to engage disc shoulders (18) configured in a first stage of the turbine engine. The aft air separator member (10) is constrained from movement along a radial direction by the disc shoulders engaged in the chamber of the aft air separator member. A forward air separator member (12) is affixed at a forward end thereof to a torque tube (20) to constrain movement along the radial direction. The forward air separator includes at an aft end thereof a flange (22) that engages the aft air separator member. The forward air separator member is constrained from outward radial movement along the radial direction by way of a recess (24) constructed in a portion of the aft air separator member.

Abstract: A rotor for a turbine engine. The rotor may include an assembly of axially-bolted compressor disks (14). A compressor torque tube (30) is connected to the assembly of compressor disks (14). The rotor may further include an assembly of axially-bolted turbine disks (22). A turbine torque tube (32) is axially connected to the assembly of turbine disks (22). A marriage coupling (34) is arranged to interconnect the respective torque tubes (30, 32). The marriage coupling includes a flange joint arranged to decouple the compressor torque tube or the turbine torque tube so that individual and separate access can be provided to the respective assemblies of compressor disks and turbine disks.

Abstract: A sealing band for use in a turbomachine having a plurality of stages, each stage comprising a rotatable disk and blades carried thereby. At least one pair of adjacent rotatable disks define an annular gap therebetween and have respective opposing sealing band receiving slots aligned with the annular gap. The sealing band includes a plurality of seal strips located in series adjacent to one another, and adjacent seal strips include opposing end faces located in facing relationship adjacent to one another. An underlap portion is affixed adjacent to an end of at least one seal strip and extends past the end face of an adjacent seal strip, along a radially facing side of the adjacent seal strip.

Abstract: A sealing band for use in a turbomachine having a plurality of stages, each stage comprising a rotatable disk and blades carried thereby. At least one pair of adjacent rotatable disks define an annular gap therebetween and have respective opposing sealing band receiving slots aligned with the annular gap. The sealing band includes a plurality of seal strips located in series adjacent to one another, and adjacent seal strips include opposing end faces located in facing relationship adjacent to one another. An underlap portion is affixed adjacent to an end of at least one seal strip and extends past the end face of an adjacent seal strip, along a radially facing side of the adjacent seal strip.

Abstract: A sealing band is located in opposing sealing band receiving slots of adjacent turbine disks to seal an annular gap therebetween. A through hole is defined in one of the disks, wherein the through hole defines a longitudinal hole axis and extends to the sealing band receiving slot in the disk. At least one engagement feature is defined on the disk and extends laterally of the through hole, perpendicular to the longitudinal hole axis. A pin member extends through the hole and is positioned within the sealing band receiving slot passing through an opening in the sealing band for resisting movement of the sealing band relative to the disk. The pin member includes a laterally extending cooperating feature positioned in engagement with the engagement feature for retaining the pin within the opening in the sealing band.