Patent ID: 8407893
Filing Date: 2013-04-02
Classification: B23P,F02C,F05D,F23M,F23R,Y02T,Y10T

Abstract:
1. A method of repairing an annular sheet metal combustor liner of a gas turbine engine, comprising: obtaining a combustor liner having a central portion with an effusion patch extending circumferentially all around the liner, the effusion patch having effusion cooling holes covering substantially the entire patch, the effusion patch bounded on either side by at least one effusionless band free from effusion cooling holes, each band extending circumferentially all around the liner, the effusionless patches cooled using one of film cooling of an inner surface and impingement of an outer surface: cutting circumferentially around the combustor liner bands bounding the effusion patch to thereby remove a portion of the combustor liner having the effusion patch, the removed portion including a portion of said bands bounding the effusion patch; providing a replacement liner portion including an effusion patch and at least a portion of an effusionless band bounding both sides of the effusion patch; welding the replacement liner portion to the liner assembly, the weld extending circumferentially around the cut band to provide a welded effusionless band; and providing a second one of said effusionless band on each of the inner and outer liners adjacent exit ends thereof, the second of the effusionless band being provided in an at least partially overlapping relationship with a respective one of rings mounted to an outer side of the combustor liner adjacent the exit thereof for connection of the combustor liner to a gas turbine engine, the rings having a plurality of impingement holes therethrough to permit impingement cooling of the outer side of the combustor liner at the second one of said effusionless band.