Abstract: A sealing band arrangement for a gas turbine including first and second adjoining rotor disks each including a disk arm having a slot. The sealing band arrangement includes at least one first seal strip segment located within the slots, wherein the seal strip segment includes first and second ends. The sealing band arrangement also includes a tab section that extends from the first end in order to form an underlap seal with an adjacent second seal strip segment. The underlap seal enables a thickness of the first and second ends to be substantially equivalent to a thickness of the first seal strip segment in order to improve wear life of the seal strip segment. The sealing band arrangement further includes at least one wide portion formed in the first seal strip segment wherein the wide portion is wider than a remaining portion of the first seal strip segment.

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 sealing band arrangement for a gas turbine including first and second adjoining rotor disks each including a disk arm having a slot. The sealing band arrangement includes at least one first seal strip segment located within the slots, wherein the seal strip segment includes first and second ends. The sealing band arrangement also includes a tab section that extends from the first end in order to form an underlap seal with an adjacent second seal strip segment. The underlap seal enables a thickness of the first and second ends to be substantially equivalent to a thickness of the first seal strip segment in order to improve wear life of the seal strip segment. The sealing band arrangement further includes at least one wide portion formed in the first seal strip segment wherein the wide portion is wider than a remaining portion of the first seal strip segment.

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.