Method of repairing a gas turbine engine combustor
US8407893B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jul 15, 2011 |
| Grant date | Apr 2, 2013 |
| Priority date | — |
| Expiry date | Jul 15, 2031 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49346
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A method of repairing an annular sheet metal combustor liner of a gas turbine engine includes cutting circumferentially around combustor liner bands bounding an effusion patch extending circumferentially around the liner, the effusion patch having effusion cooling holes and being bounded on either side by at least one effusionless band free from effusion cooling holes, to thereby remove a portion of the combustor liner having the effusion patch. A replacement liner portion including an effusion patch is provided and welded to the liner assembly, the weld extending circumferentially around the cut band to provide a welded effusionless band. The welded effusionless bands is cooled during engine use using one of film cooling of an inner surface of the welded effusionless band and impingement cooling of an outer surface of the welded effusionless band.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.