Air cylinder type contact displacement sensor group-based aero-engine low-pressure turbine shaft disk fastening force detection method and device

Abstract

The invention discloses an air cylinder type contact displacement sensor group-based aero-engine low-pressure turbine shaft disk fastening force detection method and device. The detection method includes the following steps that: the relations between the pre-tightening forces of the bolts of a low-pressure turbine, and the relative displacement and distribution of an upper disk surface and a lower disk surface are obtained; the relative displacement of the upper disk surface and the lower disk surface of the shaft disk structure of the low-pressure turbine in an assembling process or after assembling is detected; and whether the pre-tightening forces of bolts to be tested or the pre-tightening forces of adjacent bolts are insufficient or too large is judged, and bolts of which the pre-tightening forces are unreasonable are determined, and the deviation values of the pre-tightening forces are determined. With the detection method and device of the invention adopted, the pre-tightening states of the bolts can be judged fast and accurately; the structures of the bolts are not required to be damaged in a measurement process; the accuracy of the method and device is higher than a current mode according to which the length of short bolts is directly measured; the axial displacement deviation of the disk surfaces which is caused by sensor feeding error can be eliminated; the influences of disk surface coordinate datum offset in a fastening process can be decreased; and repeated positioning deviation of repeated measurement can be eliminated.

Description

technical field [0001] The invention belongs to the assembly technology of aero-engines, and in particular relates to a method and a device for detecting the fastening force of a low-pressure turbine shaft disk of an aero-engine based on a cylinder-type contact displacement sensor group. Background technique [0002] The low-pressure turbine of an aeroengine is a structure that transmits the power of the low-pressure turbine disk to the fan. It has a high operating speed and a large transmission torque value. The assembly work of the low-pressure turbine shaft disk is mainly composed of bolt tightening operations. The tightening process parameters such as tightening force, tightening sequence, and tightening times will affect the pre-tightening force of the bolts, and then affect the contact stress of the shaft-disk connection interface and the surface of the disk. Deformation and low-pressure turbine shaft coaxiality, low-pressure turbine shaft disc dynamic stiffness and dy...

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Problems solved by technology

On the other hand, the connection structure of the low-pressure turbine shaft disk of an aero-engine is a flange surface with an outer diameter of several hundred millimeters. Dozens of bolts are used for connection. It is inefficient to test the displacement of the entire disk surface. How to quickly and accurately determine the value of each bolt The preload state is also a problem that needs to be solved in practical applications

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