An aero-engine blade damage online identification method

Abstract

The invention belongs to the technical field of aero-engine fault diagnosis, and relates to an aero-engine blade damage online identification method. Comprising the following steps: establishing a damage-free blade finite element model, and calculating modal frequency and vibration mode of each order; establishing a non-damage blade test model, and identifying test modal frequency and vibration mode; taking the previous 10-order test modal frequency as a target value, taking the blade material parameter as a variable, correcting the blade finite element model, obtaining an accurate finite element model, and calculating a stiffness matrix of each element, where the unit stiffness matrix is assembled into an overall vibration mode stiffness matrix; measuring blade vibration parameters in a working state; reading vibration parameters and rotating speed parameters in real time through an online monitoring system, correcting the finite element model to complete damage positioning, calculating the modal strain energy change rate to complete damage evaluation, and displaying an alarm when the damage amount exceeds the limit. The blade damage position and the damage degree can be determined online to complete feedback, serious faults are prevented, the repair cost is reduced, and the flight safety is guaranteed.

Description

technical field [0001] The invention belongs to the technical field of aeroengine fault diagnosis and relates to an online identification method for aeroengine blade damage. Background technique [0002] Aeroengines work in the harsh environment of high temperature, high pressure, and high speed, which can easily cause damage to parts. Blades, especially rotor blades, as important components of aero-engines, are subject to multiple loads such as temperature, centrifugal force, aerodynamics, and vibrations, and are prone to fatigue cracks. Engine performance and safety. [0003] Aeroengine is a complex system, and it is difficult to identify the specific fault location and damage degree by monitoring the vibration characteristics of the whole machine under working conditions. The existing aero-engine blade damage identification technology is to disassemble the engine for fault inspection after the fault occurs, and determine the fault location and shape of the blade through...

AI Technical Summary

Problems solved by technology

The existing aero-engine blade damage identification technology is to disassemble the engine for fault inspection after the fault occurs, and determine the fault location and shape of the blade through optical detection means. This is an after-the-fact detection method, which greatly increases the cost of maintenance support ; The second is based on laboratory health monitoring, there is no automatic alarm effect for aero-engine blade damage identification that can be applied to actual test runs and flights

Images