FIELD: engine building.
SUBSTANCE: invention relates to the gas turbine engine and, in particular, to its bearing (support) structure. Gas turbine engine maintenance method includes its bearing compartment disassembling and providing access from the gas turbine engine front part to the located in the bearing compartment gearbox. Gas turbine engine has axial circuit, passing from the engine front side backwards, in accordance with the axial flow direction. Maintenance method includes the component servicing, which is located in the bearing compartment. Another embodiment of the proposed method comprises accessing from the front central assembly front part to the gearbox, driven by the low-speed shaft, and the component servicing, which is located in the bearing compartment behind the front central assembly.
EFFECT: invention allows to facilitate the gas turbine engine rapid maintenance.
26 cl, 8 dwg
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