A method for analyzing the nonlinear vibration characteristics of a turbine mechanical blade considering the friction and collision of a damping structure

A nonlinear vibration and turbomachinery technology, applied in special data processing applications, instruments, electrical digital data processing, etc., can solve problems such as low computing efficiency and achieve the effect of improving computing efficiency

Active Publication Date: 2019-03-01
XI AN JIAOTONG UNIV
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Problems solved by technology

[0004] The purpose of the present invention is to provide a method for analyzing the nonlinear vibration characteristics of turbomachinery blades considering the friction of damping structures, aiming at the calculation and analysis of the vibration characteristics of turbomachinery blades under nonlinear dry friction damping, to solve the above-mentioned problems in the prior art The computational inefficiency of the

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  • A method for analyzing the nonlinear vibration characteristics of a turbine mechanical blade considering the friction and collision of a damping structure
  • A method for analyzing the nonlinear vibration characteristics of a turbine mechanical blade considering the friction and collision of a damping structure
  • A method for analyzing the nonlinear vibration characteristics of a turbine mechanical blade considering the friction and collision of a damping structure

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Embodiment Construction

[0027] see figure 1 As shown, the present invention provides a method for analyzing nonlinear vibration characteristics of turbomachinery blades considering damping structure friction, comprising the following steps:

[0028] 1) According to the geometric structure of the actual turbine blade-disc, establish a three-dimensional model of the turbine blade-disc, and divide the three-dimensional model to form an overall finite element model of the turbine blade-disc;

[0029] 2) Determine the contact interface and friction node pairs of each damping structure of the blade-disk finite element model, and perform static contact analysis. The specific steps are:

[0030] (2.1) Determine the number p of friction node pairs at the contact interface of each damping structure of the blade-disk finite element model. The contact interface should include all friction interfaces, including the contact surface of adjacent blade shrouds and the contact surface between lamellae .

[0031] see...

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Abstract

The invention provides a method for analyzing the nonlinear vibration characteristics of a turbine mechanical blade considering the friction and collision of a damping structure, and the method comprises the following steps of: obtaining the vibration characteristics of the turbine mechanical blade through a finite element method; after the time domain linear finite element dynamic equation of thedisk system, the degree of freedom is reduced by the modal synthesis method to obtain the time domain linear reduction finite element dynamic equation, and then the frequency domain linear reductionfinite element dynamic equation is obtained by the multi-harmonic balance method. The non-linear force vectors on the blade-finite element model of the disk due to contact friction are determined by the Coulomb dry friction model and transformed into turbine blades in the frequency domain. Nonlinear force vectors at all nodes of the roulette disk finite element model, thereby obtaining Nonlinear Reduction Finite Element Dynamics Equation of turbomachinery-Disk in Frequency Domain; then the solution is to draw the turbine blades The frequency response curve of the roulette disc. The invention greatly reduces the calculation time and the calculation cost, thereby greatly improving the efficiency.

Description

technical field [0001] The invention belongs to the field of turbomachinery design, in particular to a method for analyzing nonlinear vibration characteristics of turbomachinery blades. Background technique [0002] As an important equipment for energy conversion, turbomachinery plays an important role in modern society, and it is of great significance to ensure the safe operation of turbomachinery. As a key component of turbomachinery blade, its failure problem has become the main reason for turbomachinery failure. The working environment of turbomachinery blades is harsh, especially when the blades vibrate under the action of airflow excitation force. High cycle fatigue caused by local large vibration stress is one of the main reasons for blade failure. At present, an effective method to reduce the vibration level of the blade is to increase the blade damping, and the most widely used method to increase the blade damping is to increase the dry friction damping. The frict...

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Application Information

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