Methods for replacing combustor liners

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 compr...

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Bibliographische Detailangaben
Hauptverfasser:	MOERTLE, GEORGE, E, EMILIANOWICZ EDWARD JOHN, PELLETIER SCOTT HOWARD
Format:	Patent
Sprache:	eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBINED OPERATIONS COMBUSTION APPARATUS COMBUSTION ENGINES COMBUSTION PROCESSES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS GAS-TURBINE PLANTS GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MACHINE TOOLS MECHANICAL ENGINEERING METAL-WORKING NOT OTHERWISE PROVIDED FOR OTHER WORKING OF METAL PERFORMING OPERATIONS TRANSPORTING UNIVERSAL MACHINE TOOLS WEAPONS
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Beschreibung
Zusammenfassung:	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.