Methods for replacing combustor liners

Details Methods for replacing combustor liners Methods for replacing combustor liners

B - Operations, Transporting

23

P

B23P 6/00 (2006.01) F02C 7/00 (2006.01) F23R 3/00 (2006.01) F23R 3/08 (2006.01) F23R 3/42 (2006.01)

Patent

CA 2451303

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 liner liners. The method comprises cutting through at least one of the combustor inner and outer liner 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.

Méthode de remplacement de la chemise de chambre de combustion d'un turbomoteur (40). La chambre de combustion (30) comprend une zone de combustion (36) formée par des chemises intérieure et extérieure (42 et 44). Plusieurs éléments de refroidissement (88) sont formés par des parties en surplomb (84) des chemises intérieure et extérieure. La méthode consiste à couper, à l'arrière d'une partie en surplomb, au moins une des chemises de la chambre de combustion. La partie (124) de la chemise de chambre de combustion en amont de la coupure (122) reste couplée dans la chambre de combustion. La partie de la chemise de chambre de combustion à l'arrière de la coupure est retirée, puis une chemise de remplacement est installée dans la chambre de combustion de manière à ce que la nouvelle chemise dépasse l'arrière de la partie de la chemise de chambre de combustion qui est en amont de la coupure.

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