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Vibration stress numerical analysis method for turbomachinery blades

A technology of vibration stress and turbo machinery, applied in the direction of electrical digital data processing, special data processing applications, instruments, etc.

Active Publication Date: 2017-03-22
XI AN JIAOTONG UNIV
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  • Abstract
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  • Claims
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Problems solved by technology

However, there is no relatively mature numerical analysis method for vibration stress with high calculation accuracy and fast speed in the prior art.

Method used

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  • Vibration stress numerical analysis method for turbomachinery blades
  • Vibration stress numerical analysis method for turbomachinery blades
  • Vibration stress numerical analysis method for turbomachinery blades

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Embodiment Construction

[0087] The present invention will be described in further detail below in conjunction with the accompanying drawings.

[0088] see figure 1 Shown, a kind of vibration stress numerical analysis method of turbomachinery blade of the present invention comprises the following steps:

[0089]1), given the three-dimensional model, material parameters and operating parameters of the turbomachinery blade, the FEM model of the solid region of the entire blade and the CFD model of the periodically symmetrical fluid region are respectively established in the meshing software; and the finite element The node number and node coordinates of the model, the unit number and the node number corresponding to the unit are output to the file Solid.fem; the material parameters and operating parameters are output to the file Blade.dat. Among them, the material parameters include the density, elastic modulus, and Poisson's ratio of the blade and the disc; the operating parameters include the speed o...

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Abstract

The invention discloses a vibration stress numerical analysis method for turbomachinery blades. The method comprises the steps of 1, building an FEM model of a solid region of an entire circle of the blades and CFD models of periodically symmetric fluid regions; 2, obtaining steady-state pressure intensity field distribution of meshes of the fluid regions of the blades and instant pressure intensity field distribution of each time step in a pneumatic period; 3, converting pressure intensity field distribution data; 4, performing finite element mode analysis of the entire circle of the blades; 5, obtaining node force load vectors of blade surfaces of all time steps; 6, solving a vibration displacement response by a mode superposition method; 7, expanding a displacement response result into a stress result; and 8, performing vibration stress result extraction and check. According to the method, the pressure intensity distribution of the blade surfaces is obtained by adopting a non-steady computing method, and an accurate air exciting-vibration force load is obtained by interpolation from the meshes of the fluid regions of the blades to the pressure intensity of the meshes of the solid region, so that the computing precision is improved; and each sector adopts a CPU+GPU heterogeneous parallel computing mode, so that the computing speed is greatly increased.

Description

technical field [0001] The invention belongs to the field of design and calculation of turbomachinery blades, in particular to a numerical analysis method of vibration stress of turbomachinery blades. Background technique [0002] The blades, the key components of turbomachinery, work in harsh environments such as high pressure and high speed. Therefore, the actual operation experience shows that most of the major events of turbomachinery are related to the high cycle fatigue damage caused by the vibration of the blades. The vibration stress generated under the action of force is the main cause of high cycle fatigue of the blade. [0003] With the rapid development of computer hardware and the wide application of high-efficiency numerical calculation methods, accurate numerical methods are used to calculate the vibration stress in the blade design stage. On the one hand, it greatly shortens the design cycle and saves test costs. It is of great significance for the design an...

Claims

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Application Information

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