| 摘要 |
A method enables replacement of a gas turbine engine combustor liner (40). The combustor (30) has a combustion zone (36) formed by inner and outer liners (42 and 44). A plurality of cooling features (88) are formed by overhanging portions (84) of the inner and outer liners (42, 44). The method comprises cutting through at least one of the combustor inner and outer liner (42, 44) aft of an overhanging portion, wherein the portion (124) of the combustor liner upstream from the cut (122) remains coupled within the combustor, removing the portion of the combustor liner that is aft of the cut, and installing a replacement liner within the combustor such that the replacement liner extends aftward from the portion of the combustor liner that is upstream from the cut. <IMAGE> |
