A method is provided for disassembling a gas turbine engine (20). The gas turbine engine (20) includes a compressor section (29), a combustor section (30), a turbine section (31), a static structure (36) and a bypass duct (40). The static structure (36) houses and supports the compressor section (29), the combustor section (30) and the turbine section (31). The static structure (36) includes a turbine support structure (46). The bypass duct (40) includes an inner duct wall (80), an outer duct wall (82) and a bypass flowpath (84) formed radially between the inner duct wall (80) and the outer duct wall (82). The outer duct wall (82) extends axially along the static structure (36) and overlaps the turbine support structure (46). During the method, the turbine support structure (46) is removed from the gas turbine engine (20) while the outer duct wall (82) remains installed.
GAS TURBINE ENGINE DISASSEMBLY/ASSEMBLY METHODS
GASTURBINENTRIEBWERKS-ZERLEGUNGS-/-MONTAGEVERFAHREN
PROCÉDÉS D'ASSEMBLAGE/DÉSASSEMBLAGE DE TURBINE À GAZ
2023-03-01
Patent
Electronic Resource
English
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