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.

Abstract: A seal strip assembly for use in a turbomachine having a plurality of stages including rotationally driven disks, and arms on opposed portions of adjoining disks to define paired arms with a space therebetween. The seal strip assembly includes a seal strip positioned in the space between the paired arms and having opposing edges for locating in slots formed in opposed faces of the paired arms. An anti-rotation block is provided, where a portion of the anti-rotation block is removably located in opposed openings formed in the paired arms and is engaged with the seal strip to resist movement of the seal strip relative to the paired arms. A detachable engagement member is detachably fastened to the anti-rotation block for maintaining the anti-rotation block in engagement with the seal strip.

Abstract: The turbine includes a plurality of successive stages each having a rotatable disk and blades carried thereby. A pair of adjacent rotatable disks define an annular gap therebetween and have respective opposing sealing band receiving slots aligned with the annular gap. At least one of the rotatable disks has at least one notch therein coupled to the respective sealing band receiving slot, and a sealing band is in the opposing sealing band receiving slots to seal the corresponding annular gap. The sealing band includes at least one sealing strip and at least one movable locking tang carried thereby and extending into the at least one notch to define an anti-rotational feature for the sealing band.

Abstract: A seal strip assembly for use in a turbomachine having a plurality of stages including rotationally driven disks, and arms on opposed portions of adjoining disks to define paired arms with a space therebetween. The seal strip assembly includes a seal strip positioned in the space between the paired arms and having opposing edges for locating in slots formed in opposed faces of the paired arms. An anti-rotation block is provided, where a portion of the anti-rotation block is removably located in opposed openings formed in the paired arms and is engaged with the seal strip to resist movement of the seal strip relative to the paired arms. A detachable engagement member is detachably fastened to the anti-rotation block for maintaining the anti-rotation block in engagement with the seal strip.

Abstract: This invention relates to a seal plate system adapted to fit between axially adjacent turbine blades and turbine vanes to seal a rim cavity. The seal plate system may be formed from a seal plate supported by a plurality of extended disk lugs extending from a disk. The seal plate system may also include one or more extended disk lug receiving cavities adapted to receive protrusions extending from the disc. One or more ribs may extend from the seal plate for increasing the structural integrity of the seal plate.