Patent ID: 7827686

Claim:
A method for servicing gas turbines comprises the steps of a) disassembling a gas turbine into modules and/or subassemblies and/or individual parts of the gas turbine; b) inspecting and/or repairing and/or replacing the modules and/or subassemblies and/or individual parts of the gas turbine; c) reassembling the gas turbine from the inspected and/or repaired and/or new modules and/or subassemblies; wherein at least one of steps a) and c) is divided into at least two work steps, wherein a work station is provided for performing each work step, and wherein at least one of steps a) and c) further comprise moving the gas turbine and/or modules and/or subassemblies and/or individual parts thereof through the work stations; and at each work station, performing a corresponding work step on the gas turbine and/or modules and/or subassemblies and/or individual parts; wherein the at least two work steps includes a plurality of main work steps and a plurality of secondary work steps associated with at least one of the main work steps, and wherein the step of performing includes performing the secondary work steps associated with a main work step downstream from the associated main work step for disassembly step a), and upstream from the associated main work step for assembly step c); wherein the disassembling step a) is divided into three main work steps, the gas turbine being moved consecutively through the consecutive main work stations and disassembled into its modules; and wherein the gas turbine is an aircraft engine and the aircraft engine is inspected as one unit, and wherein the disassembling step a) includes A1) removing a main fan wheel module in a first main work step at a first main work station; A2) moving the aircraft engine with the main fan wheel module removed to a second main work station, A3) removing a low-pressure turbine module and a high-pressure turbine module in a second main work step at the second main work station; A4) moving the disassembled aircraft engine from step A3) to a third main work station, A5) removing a high-pressure compressor module in a third main work step at the third main work station, wherein a fan case module remains after step A5).