Method and system for predicting remaining service life of aviation turbofan engine

Abstract

The embodiment of the invention provides a method and system for predicting the remaining service life of an aviation fanjet. The method comprises: acquiring detection data of an aviation fanjet and determining a degradation stage of the aviation fanjet according to the detection data; acquiring a feature vector corresponding to the detection data based on an empirical mode decomposition method corresponding to the degradation stage of the aviation fanjet; and inputting the feature vector corresponding to the detection data into a pre-established aviation fanjet degradation model and outputting a remaining service life predicted value of the aviation fanjet. According to the invention, the current degradation stage can be determined based on the operating state of the aviation fanjet and the remaining service life is predicted; the regular maintenance period is extended; and the operation and maintenance costs are lowered.

Description

technical field [0001] Embodiments of the present invention relate to the technical field of health management of aviation turbofan engines, and in particular to a method and system for predicting the remaining service life of aviation turbofan engines. Background technique [0002] The aviation turbofan engine is a collection of various cutting-edge technologies, and it is a symbol of the scientific and technological strength of a country's overall aviation industry. Its development is of great significance to promote the country's scientific and technological progress. However, once any part of an aviation turbofan engine fails, it may cause a catastrophe of aircraft crash and death, which will not only cause huge economic losses to the country, but also cause immeasurable negative political impact internationally. Therefore, by predicting the remaining life of the aviation turbofan engine through the change of the performance parameters, the replacement and maintenance of...

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Problems solved by technology

[0004] However, the method in the prior art is to determine the remaining service life by establishing a health index and setting a fixed failure threshold. The quality of the health index is difficult to evaluate, and the setting of the failure threshold also requires a large number of experiments.

And the established degradation model is an exponential model, which needs to be matched with the model library to determine the remaining service life of the aero-engine. The matching degree uses the standardized Euclidean distance, and the reliability of the matching results is difficult to prove

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