Patent ID: 8562000
Filing Date: 2013-10-22
Classification: F01D,F05D

Abstract:
1. A turbine combustion system transition exit seal apparatus comprising: a seal strip comprising a length, a width, an imperforate minimum thickness, a central portion with a first thickness over the length of the strip, and first and second side portions, each side portion comprising a thickness greater than the first thickness adjacent the central portion along the length of the strip; wherein the first and second side portions comprise a respective first and second series of transverse slots along the length of the strip, wherein each side portion comprises a linear array of base-in prisms separated by the respective series of transverse slots, wherein the base of each prism is oriented toward the central portion along the length of the strip, and wherein the seal strip is slidably mounted into two opposed slots in two respective adjacent turbine combustion system transition exit frames.