Patent ID: 9631507
Date: 2017-04-25
CPC Classifications: F01D,F05D

Claim:
1. A sealing band arrangement for a gas turbine, wherein the gas turbine includes first and second adjoining rotor disks separated by a gap, comprising: a seal strip segment located within the gap, wherein the seal strip segment includes first and second segment surfaces each oriented in a first direction wherein the second segment surface is spaced apart from the first segment surface to form a first raised portion that extends from the seal strip segment and wherein the first raised portion includes a first mating surface that is oriented in a second direction transverse to the first direction and wherein the first raised portion and the seal strip segment are unistructurally formed; an aperture formed in either the first or second rotor disk; and a locking pin having a single pin section and a planar section wherein the pin and planar sections include first and second pin surfaces, respectively, wherein the first and second pin surfaces are each oriented in the first direction and wherein the first pin surface is spaced apart from second pin surface to form a second raised portion that extends toward the first raised portion, wherein the second raised portion includes a second mating surface that is oriented in the second direction and abuts against the first mating surface thereby locking the locking pin and the seal strip segment together and wherein the pin section is located within the aperture to stop circumferential movement of the seal strip segment relative to the first and second disks.