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Aeroengine low pressure turbine shaft disc fastening force detection method and device based on linear laser displacement sensor set

A technology of displacement sensor and low-pressure turbine shaft, which can be used to measure the direction of torque/torsional force during tightening, which can solve the problems of low test efficiency, achieve fast detection speed, solve detection difficulties, and be easy to implement

Active Publication Date: 2017-05-31
DALIAN UNIV OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

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

Method used

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  • Aeroengine low pressure turbine shaft disc fastening force detection method and device based on linear laser displacement sensor set
  • Aeroengine low pressure turbine shaft disc fastening force detection method and device based on linear laser displacement sensor set
  • Aeroengine low pressure turbine shaft disc fastening force detection method and device based on linear laser displacement sensor set

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Effect test

Embodiment 1

[0066] A method for detecting fastening force of an aeroengine low-pressure turbine shaft disk based on a line laser displacement sensor group, the line laser displacement sensor group includes a line laser displacement sensor Ⅰ and a line laser displacement sensor Ⅱ, a line laser displacement sensor Ⅰ and a line laser displacement sensor Ⅱ Arranged in a straight line along the diameter of the disk surface of the low-pressure turbine shaft disk and the distance to the center of the disk surface of the low-pressure turbine shaft disk is S, and S is equal to the midpoint of the line connecting two adjacent bolts on the low-pressure turbine shaft disk The distance from O to the center of the disk surface of the low-pressure turbine shaft disk, the installation planes of the line laser displacement sensor I and the line laser displacement sensor II are perpendicular to each other,

[0067] The detection method has the following steps:

[0068] S1. Obtain the relationship between t...

Embodiment 2

[0098] like Figure 1-5 As shown, an aeroengine low-pressure turbine shaft plate fastening force detection device based on a line laser displacement sensor group, the line laser displacement sensor group includes a line laser displacement sensor I1 and a line laser displacement sensor II2, a line laser displacement sensor I1 and a line laser displacement sensor The displacement sensor II2 is arranged in a straight line along the diameter of the disk surface of the low-pressure turbine shaft disk 3 and the distance from the center of the disk surface of the low-pressure turbine shaft disk 3 is S, the installation plane of the line laser displacement sensor I1 and the line laser displacement sensor II2 are perpendicular to each other, wherein, S is equal to the distance from the midpoint O of the line connecting two adjacent bolts 4 on the low-pressure turbine shaft disk 3 to the center of the low-pressure turbine shaft disk 3,

[0099] The test device includes a base 5 and a V-...

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Abstract

The invention discloses an aeroengine low pressure turbine shaft disc fastening force detection method and device based on a linear laser displacement sensor set. The method comprises steps that relationships between low pressure turbine bolt pretightening force and disc surface displacement magnitude and distribution are acquired; disc surface displacement of a low pressure turbine shaft disc test piece after assembling is tested; whether to-be-detected bolts or adjacent bolts have insufficient or overlarge pretightening force is determined; the bolts with unreasonable pretightening force and pretightening force deviation values are determined. The method is advantaged in that disc surface deformation of the low pressure turbine shaft disc is detected through a linear laser displacement detection method, data acquired by a linear displacement sensor is processed, displacement difference of different parts of the disc surface on one prescribed path before and after pretightening is extracted, a deformation difference value and a deformation value generated by a desired value pretightening force value are compared to determine fastening quality, a problem of fastening quality detection difficulty of an aeroengine is effectively solved, and properties of quick detection speed, high precision and easy realization are realized.

Description

technical field [0001] The invention belongs to the assembly technology of an aero-engine, 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 line laser 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 dynamic sta...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01L5/24
CPCG01L5/24
Inventor 孙清超孟亮国黄伟强汪云龙袁博
Owner DALIAN UNIV OF TECH
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