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Method, device, and system for modal damping identification

A recognition method and a recognition device technology, which are applied in special data processing applications, instruments, electrical digital data processing, etc., can solve problems such as poor stability of damping ratio, and achieve the effect of improving recognition accuracy

Active Publication Date: 2016-03-23
CHINA AVIATION POWER MACHINE INST
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  • Abstract
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  • Application Information

AI Technical Summary

Problems solved by technology

Therefore, the stability of the frequency domain method to determine the damping ratio through the amplitude change will be poor

Method used

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  • Method, device, and system for modal damping identification
  • Method, device, and system for modal damping identification
  • Method, device, and system for modal damping identification

Examples

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Embodiment Construction

[0067] 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.

[0068] refer to image 3 , image 3 It is a schematic diagram of the installation of the rotor on the tester, wherein the rotor system installed on the tester includes a rear support 1, a turbine disc 2, a transmission shaft 3, and a balance boss 4; a front support 5; an output shaft 6; Speed ​​increaser 7 and vacuum box 8. The dynamic characteristic test of the rotor system is carried out on this tester. The whole tester consists of a high-speed end and a low-speed end, and the high-speed end and the low-speed end are respectively driven by a 400kW DC motor. The high-speed end and the low-speed end have their own speed-increasing systems, support systems and vacuum systems (in order to pre...

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PUM

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Abstract

The invention discloses a method, a device, and a system for modal damping identification. The method for modal damping identification comprises steps: obtaining amplitude-frequency data of a rotor, and phase-frequency data; according to the obtained amplitude-frequency data, drawing an amplitude-frequency curve, determining a critical rotation speed point; according to the obtained phase-frequency data, drawing and fitting a phase-frequency curve, to obtain a fitted phase-frequency curve equation; according to the fitted phase-frequency curve equation, calculating the slope of the tangent line of the critical rotation speed point in the phase-frequency curve; and according to the calculated slope, obtaining a modal damping ratio. The method for modal damping identification conveniently and accurately determines critical rotation speed from the amplitude-frequency curve. By using the slope of the tangent line of the critical rotation speed point in the phase-frequency curve and the damping ratio are in a reciprocal relationship, the modal damping ratio is identified, so as to conveniently, rapidly, and accurately obtain the modal damping ratio.

Description

technical field [0001] The invention relates to the field of aero-engines, in particular to a method and device for identifying modal damping. In addition, the present invention also relates to a system comprising the above-mentioned modal damping identification device. Background technique [0002] In the measurement of frequency, amplitude and damping of the three elements of vibration, the accurate identification of damping is the most difficult, and damping plays a very important role in the control of vibration and noise. First, damping can suppress the vibration and noise of the rotor system. Due to the vibration isolation effect of the damping, the rotor can pass the critical speed smoothly, thereby avoiding excessive vibration amplitude when passing the critical speed, which will cause the rotor and the stator to rub against each other. Secondly, when using the finite element method to calculate the dynamic characteristics of the rotor system, the damping coefficie...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/15
Inventor 边杰
Owner CHINA AVIATION POWER MACHINE INST
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