Patent ID: 6266961
Filing Date: 2001-07-31
Classification: F05B,F23R,Y02T

Abstract:
A gas turbine combustor liner comprising:a first annular panel section having a first cooling nugget formed at one end thereof;a first row of cooling holes formed in said first cooling nugget;a second annular panel section having a second cooling nugget formed at one end thereof;a second row of cooling holes formed in said second cooling nugget, said second row of cooling holes being arranged in a preferential cooling pattern comprising a plurality of arrays, wherein each said array comprises a first set of cooling holes having a first diameter and a second set of cooling holes having a second diameter that is smaller than said first diameter; andat least one igniter tower formed in said first annular panel section, said at least one igniter tower being circumferentially aligned with one of said second sets of cooling holes.