B - Operations – Transporting – 23 – P
Patent
B - Operations, Transporting
23
P
B23P 6/00 (2006.01) F02C 7/00 (2006.01) F23R 3/00 (2006.01) F23R 3/42 (2006.01) F23R 3/60 (2006.01)
Patent
CA 2450975
A method facilitates replacing a portion of a gas turbine engine combustor liner 40. The combustor includes a combustion zone 36 formed by inner and outer liners 42 and 44. The inner and outer liners each include a series of panels 50, and at least one of the inner and the outer liner includes an aft support 120 coupled to an aft end of liner. The method comprises cutting through at least one of the combustor inner and the outer liner upstream from the liner aft support, removing the combustor liner aft support from the combustor, and installing a replacement aft support within the combustor such that the liner aft support extends aft ward from the portion 144 of the combustor liner that is upstream from the cut.
Méthode qui facilite le remplacement d'une partie de la chemise de la chambre de combustion d'une turbine à gaz (40). La chambre de combustion comprend une zone de combustion (36) formée par des chemises interne et externe (42 et 44). Les chemises interne et externe comprennent chacune une série de panneaux (50), et au moins une des chemises comprend un support arrière (120) couplé à son extrémité arrière. La méthode comprend la coupe d'au moins une des chemises interne et externe de la chambre de combustion en amont du support arrière, le retrait du support arrière de la chemise de la chambre de combustion et l'installation d'un support arrière de remplacement dans la chambre de combustion, de sorte que le support arrière se prolonge vers l'arrière à partir de la partie (144) de la chemise qui est en amont de la coupe.
Company General Electric
Craig Wilson And Company
LandOfFree
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