Research on the Assembly Process Method of Aero-Engine Rotor Structure with Stopcock
In order to further investigate the possible optimisation path of the assembly process of aero-engine rotor structure with stop-port,taking the low-pressure turbine shaft-disc of turbofan aero-engine as the object of research,we investigate the influence of the two main contents of the bolt fastening strategy and the excess of the stop-port in the assembly process,so as to determine the use of the triangular fastening method for the low-pressure turbine shaft-disc of turbofan aero-engine,and set the excess of the band-port in the assembly process to 0.0％,and set the excess of the band-port in the assembly process to 0.0％.The excess of the belt stop structure in the assembly process is set to 0.1 mm.From the results of field experiments,all the main indexes of this assembly process are significantly better than the traditional assembly process,and it is expected to be gradually applied in the subsequent assembly.
aero-enginewith stoprotor structureassembly process
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