Method and system for selecting whole engine vibration measuring points

A technology of engines and complete machines, which is applied in special data processing applications, instruments, electrical digital data processing, etc., and can solve problems such as unreachable vibration monitoring

Pending Publication Date: 2022-03-01
AECC HUNAN AVIATION POWERPLANT RES INST
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  • Description
  • Claims
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Problems solved by technology

Its disadvantage is that the selection of external casing vibration measuring points is mainly based on experience. Due to the obvious differences in the structure of various types of engines, the arrangement of vibration measuring points inherited from experience may not accurately reflect the vibration characteristics of the rotor, thus failing to achieve Purpose of Vibration Monitoring

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  • Method and system for selecting whole engine vibration measuring points
  • Method and system for selecting whole engine vibration measuring points
  • Method and system for selecting whole engine vibration measuring points

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Embodiment Construction

[0066] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention more clear, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments It is a part of embodiments of the present invention, but not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

[0067] A method for selecting a vibration measuring point of an engine complete machine proposed by the present invention comprises the following steps:

[0068] Determine the principle of selection of engine vibration measurement points;

[0069] Establishing a finite element model of the complete engine;

[0070] According...

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Abstract

The invention discloses an engine complete machine vibration measuring point selection method and system, and the method comprises the steps: determining an engine complete machine vibration measuring point selection principle; establishing a finite element model of the whole engine; and according to the engine complete machine vibration measuring point selection principle and the complete machine finite element model, determining the engine complete machine vibration measuring point through complete machine vibration frequency response characteristic analysis. According to the invention, the selected whole engine vibration measuring point can better reflect the vibration characteristics (critical speed and unbalanced load change) of the rotor; more rotor vibration characteristic information can be obtained by using fewer whole engine vibration measuring points; and the selected whole engine vibration measuring point is more sensitive to the vibration characteristic change of the rotor, so that the vibration safety monitoring of the engine is facilitated.

Description

technical field [0001] The invention belongs to the technical field of engine testing, and in particular relates to a method and system for selecting vibration measuring points of a complete engine. Background technique [0002] The vibration of the whole machine is an inevitable phenomenon in the operation of the aero-engine. The additional dynamic load generated by the vibration acts on the engine components, forcing the structural materials to fatigue, thereby reducing the reliability of the engine. Considering that the unbalanced vibration of the rotor is the main source of the overall engine vibration, the monitoring of the overall vibration is mainly the monitoring of the engine rotor vibration. [0003] Since the engine rotor is located inside the engine, it is difficult to directly monitor its vibration. Therefore, vibration measuring points are generally arranged on the external casing of the engine to monitor its vibration. However, whether the selected vibration m...

Claims

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Application Information

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IPC IPC(8): G06F30/23G06F30/17G06F119/14
CPCG06F30/23G06F30/17G06F2119/14
Inventor 龙伦唐振寰王建方吕彪廖三丰卢愈
Owner AECC HUNAN AVIATION POWERPLANT RES INST
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