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Finite element element division method for blades and detection method for blades

A finite element and blade technology, applied in the field of engineering strength design and testing, can solve problems such as unsuitable division of blades, and achieve accurate force and deformation analysis

Active Publication Date: 2017-07-18
CHINA AVIATION POWER MACHINE INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0004] The main purpose of the present invention is to provide a finite element element division method for blades and a detection method for blades, so as to solve the problem that the finite element elements of the 10-node tetrahedron in the prior art are not suitable for dividing the grid of blades

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  • Finite element element division method for blades and detection method for blades
  • Finite element element division method for blades and detection method for blades
  • Finite element element division method for blades and detection method for blades

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Embodiment Construction

[0028] It should be noted that, in the case of no conflict, the embodiments in the present application and the features in the embodiments can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and examples.

[0029] According to one aspect of the present invention, a finite element unit division method for a blade is provided, the blade includes a blade pot surface and a blade back surface, and the finite element unit division method includes: Step S01: Obtain a plurality of blades along the height direction of the blade Section, each section includes the leaf back leaf shape point set on the back of the leaf and the leaf basin leaf shape point set on the leaf basin surface, multiple first points Ippi are taken in sequence on the leaf basin leaf shape point set, Take a plurality of second points Ippi' in order on the leaf back leaf shape point set, the second point Ippi' taken on the leaf back leaf ...

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Abstract

The invention provides a finite element unit partitioning method for a blade and a detection method of the blade. The finite element unit partitioning method includes the following steps that a plurality of grid nodes are selected to constitute a hexahedron which forms a finite element unit, and the blade is partitioned into a plurality of connected finite element units. By the adoption of the finite element unit partitioning method, the finite element units which are the hexahedrons each composed of 20 nodes are formed through partitioning according to the length, width and thickness of the blade, and therefore the structure of the blade can be simulated better, stress and deformation analysis of the blade simulated by the finite element units is more accurate and approximates to real situations of the blade, and engineers can easily find defects of the blade in time and accordingly overcome the defects in time.

Description

technical field [0001] The invention relates to the technical field of engineering strength design and detection, in particular to a finite element unit division method for blades and a blade detection method. Background technique [0002] Blades include axial flow fan blades, compressor blades, centrifugal blades and axial flow turbine blades, etc., all of which are irregular in shape, so it is necessary to cooperate with finite element analysis to test the blades when designing the blades. [0003] The existing finite element analysis divides the structure to be analyzed into multiple parts such as figure 1 The finite element element of the 10-node tetrahedron shown is relatively simple, but the calculation error based on the finite element element is relatively large, so it is not suitable for blade structure analysis. Contents of the invention [0004] The main purpose of the present invention is to provide a finite element element division method for blades and a det...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01B21/32G06F17/50G06F19/00
CPCG01B21/32G01M13/00G06F30/23
Inventor 蔡显新米栋钱正明
Owner CHINA AVIATION POWER MACHINE INST