Patent ID: 6986201
Filing Date: 2006-01-17
Classification: B23P,F23R,Y02T,Y10T

Abstract:
1. A method for replacing a gas turbine engine combustor liner, the combustor having a combustion zone formed by inner and outer liners, the inner and outer liners each including a plurality of cooling features formed by overhanging portions of the inner and outer liner liners, said method comprising: cutting through at least one of the combustor inner and outer liner aft of an overhanging portion, such a portion of the combustor liner upstream from the cut remains coupled within the combustor; removing the portion of the combustor liner that is aft of the cut; 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; and coupling a replacement liner including a downstream end that includes a support flange, within the combustor.