Blade-disc structure coupling vibration characteristic analysis method

A technology of coupled vibration and characteristic analysis, applied in image data processing, 3D modeling, instruments, etc., can solve problems such as easy to cause vibration failure, incomplete vibration analysis of blade-disk system, affecting the reliable operation of aero-engine, etc. Calculation time, effect of reducing solution size

Pending Publication Date: 2020-05-05
CIVIL AVIATION FLIGHT UNIV OF CHINA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The technical problem to be solved by the present invention is to provide a method for analyzing the coupled vibration characteristics of the blade-disk structure in order to solve the above-mentioned background technology. The blade-disk structure is used as a complete coupling system to calculate and analyze its vibration characteristics, which makes the vibration analysis of the blade-disk system incomplete during the working process, which is likely to cause vibration failures and affect the reliable operation of the aero-engine.

Method used

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  • Blade-disc structure coupling vibration characteristic analysis method
  • Blade-disc structure coupling vibration characteristic analysis method
  • Blade-disc structure coupling vibration characteristic analysis method

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Embodiment 1

[0026] Example 1, as figure 1 As shown, the present invention provides a technical solution: a method for analyzing the coupled vibration characteristics of a blade-disk structure, comprising the following steps:

[0027] S1. Determine the basic repeating sector of the leaf-disk structure, extract the geometric parameters of the basic repeating sector, and the geometric parameters of the repeating sector for the leaf-disk structure include the blade blade body, the blade root platform, the tenon, the roulette body, the disk According to the size parameters of edge, bolt hole and tongue and groove, enter the DesignModeler interface in the Geometry module of the finite element software ANSYS Workbench to perform modeling operations, and establish a 3D solid model of the basic repeating sector of the leaf-disk structure;

[0028] S2. Enter the Modal modal analysis module of ANSYS Workbench to establish a 3D finite element model of the cyclic symmetrical structure. Since the leaf-...

Embodiment 2

[0035] Embodiment 2, the present invention provides a technical solution: a method for analyzing the coupled vibration characteristics of a blade-disk structure, comprising the following steps:

[0036] S1. Select the third-stage blade-disc structure of a high-pressure compressor of an engine as the analysis object, such as figure 2 As shown, there are 60 working blades on the outer edge of the roulette, so the sector structure with an included angle of 6° is taken as the basic repeating sector, ignoring some small structures such as the snap ring grooves on the front and rear surfaces of the tongue and groove that have little effect on the calculation results , enter the DesignModeler interface in the Geometry module of the finite element software ANSYS Workbench to perform modeling operations, and establish a 3D model of basic repeating sectors;

[0037] S2. Enter the Modal modal analysis module of ANSYS Workbench to establish a 3D finite element model of a cyclically symme...

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Abstract

The invention provides a blade-disc structure coupling vibration characteristic analysis method. The specific method is as follows: based on a cyclic symmetry structure modal analysis basic theory, firstly, size parameters of a basic repeated sector of a blade-disc structure are extracted, the three-dimensional solid model of the basic repeated sector of the blade-disc structure is established based on a mature finite element software ANSYS Workbench platform, and the three-dimensional finite element model of the cyclic symmetry structure is established; and after analysis, a blade-disc integral structure coupling vibration rule is found. The traveling wave pitch diameter vibration frequency of the blade-disc integral structure is further calculated, the method aims at an exciting force source when a blade-disc structure works in an actual engine, the resonance characteristics of traveling wave pitch diameter vibration are analyzed, whether resonance occurs or not is judged, comprehensive analysis of the coupling vibration characteristics of the blade-disc overall structure is completed, vibration faults of the blade-disc structure in the working process of the engine are avoided,and reliable work of the aero-engine is guaranteed.

Description

technical field [0001] The invention belongs to the technical field of blade-disc vibration analysis methods, and in particular relates to a blade-disc structure coupling vibration characteristic analysis method. Background technique [0002] The compressor is the core component of the aero-engine. It is composed of working impellers and rectifier rings alternately arranged. The working impeller is composed of a disc and several blades installed on the outer edge of the disc, also called a blade-disc system. In order to reduce the weight of the compressor rotor, the thin-disk structure is commonly used in the high-pressure compressor of the modern high-bypass ratio turbofan engine. [0003] The blade-disc system works under the conditions of high centrifugal load and high alternating aerodynamic load. The thin disc itself vibrates seriously, which has a great influence on the vibration characteristics of the outer edge blades. coupled vibration. In addition, the rotational...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/15G06F30/23G06T17/00G06F119/14
CPCG06T17/00Y02T90/00
Inventor 魏武国杨琦
Owner CIVIL AVIATION FLIGHT UNIV OF CHINA
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