An assembly method of an aeroengine low-pressure turbine shaft-disk assembly

Abstract

The invention discloses an assembling method for a low-pressure turbine shaft-disc assembly of an aero-engine. The assembling method comprises the following steps that workpieces are installed, the position and the posture of a turbine shaft are adjusted; the turbine shaft butts joint and is pre-installed; an indexable tightening system is fed to a front end operation area; a tightening shaft is tightened; and the indexable tightening system returns back. According to the assembling method for the low-pressure turbine shaft-disc assembly of the aero-engine, an assembly mode that an axis of a low-pressure turbine shaft-disc is horizontal is adopted, the position and the posture of the low-pressure turbine shaft with the large length are adjusted precisely and advantageously in the butt-joint process, centering positioning alignment and end face correct close fitting of the turbine shaft relative to a connecting disc are achieved, and the butt-joint and assembling precision is improved;a turbine shaft position and posture adjusting table is applied, quantitative position and posture adjusting is conducted on the low-pressure turbine shaft through a mechanical way, experiential methods such as traditional manual hanger operating are replaced, manual repeated trial assembly and correction are avoided, the butt-joint efficiency is improved, and assembly consistency requirements ofassemblies are met; and the indexable tightening system is adopted, worker skill requirements and the labor intensity are reduced, and the tightening efficiency is improved.

Description

technical field [0001] The invention belongs to the technical field of automatic assembly, in particular to an assembly method of a low-pressure turbine shaft-disk assembly of an aeroengine. Background technique [0002] In an aero-engine, the low-pressure turbine shaft is assembled with the connection plate at the end of the low-pressure turbine unit body through the tail end flange structure to realize the power transmission of the low-pressure turbine rotor. Due to the large external load on the low-pressure turbine rotor, the shaft-disk assembly bears tens of tons of axial force and tens of thousands of Nm of transmission torque, and its connecting part is a key vulnerable position with sudden change in cross-section, so the shaft-disk assembly Assembly performance is an important factor affecting the reliability of engine operation. [0003] During the assembly process of the low-pressure turbine shaft-disc assembly, the relative posture and posture of the low-pressure...

AI Technical Summary

Problems solved by technology

The above-mentioned assembly method has the following disadvantages: (1) It is difficult to ensure the docking accuracy: the axial dimension of the turbine shaft with a length of about 2m is too large, and the vertical lifting method makes its micro-displacement alignment difficult, which affects the centering accuracy of the components; It is difficult to adjust the posture of the vertical turbine shaft through the mechanical mechanism, and it is impossible to realize the flexible assembly requirements to adapt to the surface error of the paired contact surface, and it is difficult to ensure that the connection contact surface is correctly and tightly fitted; the assembly process relies heavily on the experience of workers, resulting in the The assembly consistency is poor; (2) The feeding of the tightening system is difficult: due to the vertical assembly method, the overall height of the components is large, and the tightening system is difficult to feed axially from top to bottom, and the mechanical arm is used as the lateral feeding mechanism of the tightening shaft (3) Subsequent assembly operations are difficult: the assembled low-pressure turbine rotor is vertical, and in the subsequent engine assembly process including its assembly with the core engine, the low-pressure turbine rotor is required The axis always maintains a horizontal position, and it is difficult to implement the turning process of the low-pressure turbine rotor of a large engine from vertical to horizontal, which requires strict requirements on the plant and equipment; (4) The existing assembly method has low operating efficiency: a large number of repeated trial assemblies rely on manual labor and correction, resulting in low assembly efficiency; the vertical assembly method of the low-pressure turbine rotor is inconsistent with the axis level requirements in the subsequent assembly processes, which affects the overall assembly efficiency

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