GAS TURBINE ENGINE Russian patent published in 2015 - IPC F01D5/06 F01D5/10 

FIELD: engines and pumps.

SUBSTANCE: gas turbine engine includes fan and LP compressor, their impellers are installed on common shaft using the axial bolts with nuts. On the axial bolts between the nut and flange for the fan impeller securing in the shaft the balance elongated inserts are installed, in their internal cavity there is transition area from thread part of the bolt shank to the cylindrical part. The bolt heads are secured around their axis by the labyrinth flange, and in axial direction by ring installed on the fan shaft using the intermediate inserts. Ratio of the balance insert OD and diameter of the cylindrical part of the bolt shank is 1.2…3, ratio of the cylindrical part of the bolt shank to length of the balance insert is 1.0…3, and ratio of length of intermediate insert to the length of bolt head is 1…1.2.

EFFECT: invention increases reliability of the gas turbine engine due to exclusion of the fan rotor unbalance, and increasing of tightening reliability and axial lock of the bolts securing the fan and LP compressor impellers to the fan shaft.

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