A method for analyzing natural frequency characteristics of turbomachinery blades based on cpu+gpu heterogeneous parallel computing

A turbomachinery, natural frequency technology, applied in the direction of calculation, geometric CAD, design optimization/simulation, etc., can solve problems such as uncomfortable calculation amount and complicated operation, and achieve the effect of reducing calculation time and improving calculation speed.

Active Publication Date: 2018-10-30
XI AN JIAOTONG UNIV
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Problems solved by technology

[0003] At present, there is no software dedicated to the analysis of the frequency characteristics of turbomachinery blades. The traditional general-purpose finite element software is too cumbersome for the analysis of complex components such as turbomachinery blades. With the improvement of engineering design requirements for calculation accuracy, As well as the deepening of the research on the whole ring of detuned blades, more nodes and units (tens of millions of levels) have to be used to simulate the actual blades. The calculation speed of general finite element software is no longer suitable for handling such a huge amount of calculations.

Method used

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  • A method for analyzing natural frequency characteristics of turbomachinery blades based on cpu+gpu heterogeneous parallel computing
  • A method for analyzing natural frequency characteristics of turbomachinery blades based on cpu+gpu heterogeneous parallel computing
  • A method for analyzing natural frequency characteristics of turbomachinery blades based on cpu+gpu heterogeneous parallel computing

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Experimental program
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Effect test

example 1

[0104] Example 1 Take a whole circle of free blades (without connectors) as an example. The three-dimensional model has a dovetail-shaped blade root and a rim, with a total of 43 blades. image 3 In (a) the geometric model of the entire blade is given, and (b) is a schematic diagram of the dovetail-shaped blade root-rim contact surface. The material parameters of the blade and the rim are shown in Table 1. Mesh generation is done in ANSA software, image 3 In (c) the local finite element mesh model, the main body of the mesh adopts 8-node hexahedral elements, and the transition part of the blade root uses tetrahedron and degenerate elements for meshing. The whole has a total of 760,885 elements and 728,400 nodes.

[0105] Table 1 Material properties of a free blade and rim

[0106]

[0107] A centrifugal load with a working speed of 3000r / min is applied to the blade for prestress analysis; the cell matrix is ​​calculated on the CPU (Intel Xeon E5-2650) and GPU (Nvidia Tesl...

example 2

[0112] Example 2 Taking a whole circle of blades with connectors (shroud and damping block) as an example, the 3D model uses fungal leaf roots, and the whole circle of blades is connected through the contact of the damping block and the shroud, a total of 92 blades , Figure 6 (a) shows the geometric model of the entire circle of the blade, (b) is a schematic diagram of the connecting parts (shroud and damping block), and the material parameters of the blade and the rim are shown in Table 3. Mesh generation is done in ANSA software, Figure 6 (c) is the local finite element mesh model of the blade. The main body adopts 8-node hexahedral elements, and the transition part between the blade root and the shroud adopts tetrahedron and degenerate elements for meshing. The total number of nodes in the overall model is 1176877. The total number of units is 1,337,312.

[0113] Table 3 Material properties of a blade and rim with connectors

[0114]

[0115] A centrifugal load with...

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Abstract

The invention provides a CPU+GPU heterogeneous parallel computing based natural frequency characteristic analysis method for a turbomachinery blade. The method comprises the steps of firstly, establishing a finite element model according to a three-dimensional model and material parameters of a to-be-analyzed turbomachinery blade, and performing pre-stress analysis on the blade; secondly, performing blade grid data preprocessing, simultaneously calculating a rigidity matrix and a mass matrix of each unit in a CPU and a GPU, and assembling the rigidity matrix and the mass matrix into total rigidity and mass matrixes; setting constraint conditions of the blade and a rim, wherein the setting process comprises constraint of rigid and elastic displacement of a boundary, contact coupling of a blade root and the rim or contact coupling of connecting pieces and correction of the total rigidity matrix; thirdly, extracting generalized eigenvalues and eigenvectors of the total rigidity and mass matrixes by using a CPU+GPU heterogeneous parallel algorithm; fourthly, converting the eigenvalues and eigenvectors into a frequency and a vibration mode of the blade, and performing output; and finally, judging a vibration type of a natural vibration mode, and drawing frequency curve distribution, a vibration safety graph or a Campbell chart of the blade according to the vibration type.

Description

technical field [0001] The invention belongs to the field of engineering design and calculation, and in particular relates to a method for analyzing natural frequency characteristics of turbomachinery blades based on CPU+GPU heterogeneous parallel computing. Background technique [0002] In recent years, due to the powerful floating-point computing capability of GPU and its rapid development at a speed exceeding Moore's Law of CPU, GPU-based parallel algorithms have rapidly become one of the research hotspots in the field of high-performance computing. The traditional finite element parallel computing methods commonly used in engineering mainly use parallel processing technologies such as distributed computing, parallel computers or multi-threading at the technical level, or use GPU on a single computing node to solve general problems such as linear equations. Local acceleration, for many specific problems in the engineering field, the acceleration effect is very limited. ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F17/50
CPCG06F30/17G06F30/23
Inventor 谢永慧刘天源张荻
Owner XI AN JIAOTONG UNIV
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