Damage Analysis and Life Prediction Method for Aeroengine Hardware Based on Damage Baseline

Abstract

The invention provides an aeroengine hardware damage analysis and service life prediction method based on a damage base line. A damage database is built according to engine manual regulations and engine structure definition standard damage description rules; a damage base line model based on a linear degradation rail is built, the linear fitting is carried out on the damage data of a fleet engine, and the maximum likelihood estimation is used for solving the damage base line model parameter estimation values; the damage data of the newly obtained single engine is used for updating the damage sign model to obtain the damage increase model of the single engine; the probability density distribution function of the hardware damage increase model, i.e. the probability density distribution function of the engine rest wing time is solved for the solved hardware damage increase model of the single engine, and a median value of the probability density distribution function is taken to be used as the rest wing service life of the engine. Through the aeroengine hardware damage analysis and service life prediction method, the prediction on the engine dismounting time of the engine by airline companies according to the hardware damage of the engine becomes possible, and further, important decision support is provided for the maintenance plan making of the engine.

Description

technical field [0001] The invention relates to an aeroengine hardware damage analysis and life prediction method based on a damage baseline, and belongs to the technical field of aeroengine detection. Background technique [0002] Aeroengine hardware damage may lead to a decline in engine efficiency and even catastrophic accidents. The safety of engine use is an important factor that determines whether an aeroengine can be used safely. The hardware damage of the aero-engine is mainly caused by the core components of the engine, namely the compressor, combustion chamber, turbine and other core components. Since the core engine of an aero-engine usually works under extreme working conditions such as high pressure and high temperature, hardware damage such as cracks and ablation often occurs. [0003] Analyzing the development trend of aero-engine hardware damage, and then effectively predicting the remaining time on wing of the engine with hardware damage, can provide an imp...

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Problems solved by technology

[0004] The purpose of the present invention is to solve the problem that the number of samples of engine borehole detection data obtained in practice is relatively small, and all obtained data are non-failure data. The Problem of Efficient Prediction at Wing Time

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