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Rotor crack fault detection method based on interval control strategy

A rotor crack and interval control technology, which is applied in the field of aero-engines, can solve the problem of low success rate of rotor cracks and achieve the effect of improving the success rate

Inactive Publication Date: 2019-08-16
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0007] In order to solve the problem that the success rate of existing rotor crack fault detection is not high, the present invention provides a rotor crack fault detection method based on an interval control strategy

Method used

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  • Rotor crack fault detection method based on interval control strategy
  • Rotor crack fault detection method based on interval control strategy
  • Rotor crack fault detection method based on interval control strategy

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specific Embodiment approach 1

[0023] Specific implementation mode one: combine figure 1 To illustrate this embodiment, the rotor crack fault detection method based on the interval control strategy given in this embodiment specifically includes the following steps:

[0024] Step 1. Select the low-pressure part of the dual-rotor structure of the aero-engine to establish a single-rotor system model, and establish a coordinate system; the coordinate system takes the endpoint where the rotor coincides with the center of mass of the aircraft as the origin o, and is firmly connected with the aircraft body. The rotor coordinate system is also the aircraft body Coordinate system, the x-axis of the coordinate system is parallel to the longitudinal axis of the aircraft fuselage, pointing to the forward direction of the aircraft, the y-axis is located in the symmetry plane of the aircraft, perpendicular to the ox-axis, pointing directly above the aircraft, and the oz-axis forms with the ox-axis and y-axis right-handed...

specific Embodiment approach 2

[0031] Specific embodiment 2: The difference between this embodiment and specific embodiment 1 is that the rotor system dynamics model described in step 3 is specifically:

[0032]

[0033] exist figure 2 In the rotor system model shown, considering a crack at the packing and considering a constant excitation in the y direction, a rotor system dynamics model such as formula (1) is established. Among them, m is the mass of the turntable, c is the damping, and c=2ξmω, ξ is the damping ratio; ω is the speed, △k is the crack stiffness, indicating the influence of the crack depth on the stiffness of the rotating shaft; k is the support stiffness of the rotor system; y is The y-axis coordinate of the center of mass of the turntable, are the first-order derivative and second-order derivative of y respectively; t is time, z is the z-axis coordinate of the center of mass of the turntable; e is the distance from the eccentricity of the turntable to the center of mass of the turntabl...

specific Embodiment approach 3

[0035] Embodiment 3: This embodiment differs from Embodiment 2 in that the specific process of converting the rotor system dynamics model into a vibration response equation described in step 4 includes:

[0036] Step 41. Dimensionless the rotor system dynamics model:

[0037]

[0038] Among them, δ, s, τ, K, Y, Z are intermediate variables; ω n is the natural frequency of the system; F represents the influence of unbalanced excitation force, G represents the influence of gravity, H is the influence of external constant excitation, and its numerical value represents the multiple of external constant excitation relative gravity; in the rotor system model among the present invention, A constant excitation can be applied by electromagnetic force. The electromagnetic field environment is built on the rotor system, and the electromagnetic force is used to create a simulated overweight environment, so that constant excitation appears on the rotor system, resulting in the effect o...

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Abstract

The invention provides a rotor crack fault detection method based on an interval control strategy, belonging to the technical field of aeroengines. The method provided by the invention comprises the following steps: firstly, selecting a low pressure part of an aeroengine bi-rotor structure to build a single rotor system model, and building a coordinate system; then, calculating critical speed of revolution of an aeroengine rotor system, and setting a target control interval of the speed of revolution according to the critical speed of revolution; applying constant excitation in the target control interval of the speed of resolution in a Y axis direction of a to-be-detected part, and establishing a rotor system dynamical model; converting the rotor system dynamical model into a vibration response equation; taking each parameter as an input signal of the rotor system, taking vibration response as an output signal of the rotor system, and drawing an amplitude-frequency response curve; andfinally, judging the rotor crack fault according to the amplitude-frequency response curve. The method provided by the invention solves a problem that success rate of the existing rotor crack fault detection is not high, and the method can be used for detection of aeroengine rotor crack.

Description

technical field [0001] The invention relates to a rotor crack fault detection method and belongs to the technical field of aero-engines. Background technique [0002] With the development of society, the development of aircraft and aviation industry has been paid more and more attention by countries all over the world. As the core of providing flight power, aeroengine has a complex structure and is easily affected by factors such as vibration and temperature. It has always been a hot topic in the aviation field. Cracks are an important fault form of engine rotors, and the study of cracks is of great significance in the production design, product testing and maintenance of engines. [0003] The existing crack models mainly include: square wave model (Han Jie, Zhang Ruilin. Fault mechanism and diagnosis technology of rotating machinery [M]. Beijing: Mechanical Industry Press, 1997). to represent; the cosine wave model proposed by Schmied (Schmied J.Vibration behavior of a tu...

Claims

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Application Information

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IPC IPC(8): G05B23/02
CPCG05B23/0221G05B2219/24065
Inventor 侯磊任双兴靳宇宏李凌峰昌泽元姚迟森
Owner HARBIN INST OF TECH
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