Aero-engine complete machine residual life prediction method based on gas path performance parameter graphic matching

A technology for aero-engine and life prediction, which is applied in the fields of electrical digital data processing, computer-aided design, special data processing applications, etc., can solve the problem of difficulty in accurately predicting the remaining life of the aero-engine, and achieves good robustness and high prediction accuracy. Effect

Active Publication Date: 2016-11-30
BEIHANG UNIV
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Problems solved by technology

[0004] The technical problem to be solved in the present invention is: Aiming at the problem that the remaining life of an aero-engine is difficult to a

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  • Aero-engine complete machine residual life prediction method based on gas path performance parameter graphic matching
  • Aero-engine complete machine residual life prediction method based on gas path performance parameter graphic matching
  • Aero-engine complete machine residual life prediction method based on gas path performance parameter graphic matching

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Embodiment Construction

[0023] The present invention will be further described below in conjunction with the accompanying drawings and specific embodiments.

[0024] Such as figure 1 As shown, a method for predicting the remaining life of an aero-engine based on graph matching mainly includes the following steps:

[0025] The first step is to construct the engine performance degradation dictionary. By processing the historical data of the engine that has been running to failure, the degradation mode dictionary that can be referred to in the prediction is obtained. First, the sensor parameters with obvious rising or falling trends are selected to characterize the performance degradation of the engine. Secondly, the dimension reduction method is used to reduce the dimensionality of the data to obtain a one-dimensional performance degradation curve. Finally, the performance degradation data of these reference engines are stored according to certain specifications, which is convenient for subsequent r...

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Abstract

The present invention provides an aero-engine complete machine residual life prediction method based on gas path performance parameter graphic matching to solve the problem that an aero-engine complete machine residual life is difficult to predict accurately. First, a degradation mode dictionary is constructed by using full-life history degradation data of engines of the same type. Secondly, sensor selection and state parameter dimensionality reduction are performed on data of a to-be-predicted engine. Then, graphic matching is performed on a recession trajectory of the to-be-predicted engine and recession trajectories of reference engines in the degradation dictionary, and life estimation of the to-be-predicted engine and similarity with the reference engines are obtained. Finally, the residual service life of the to-be-predicted engine is obtained via a similarity weighting strategy. According to the method, the residual service life of the aero-engine can be accurately predicted, and life prediction has a great significance for maintenance of the engine.

Description

technical field [0001] The invention relates to the technical field of forecasting the remaining life of an aero-engine, in particular to a method for predicting the remaining life of an aero-engine based on graphic matching of air path performance parameters. Background technique [0002] With the development of the modern aviation industry, the application range of various types of aircraft has become wider and wider, and the carrying capacity of a single aircraft has become stronger and stronger, followed by higher requirements for aircraft reliability and safety. Safety, reliability and economy are the three factors most concerned by aero-engine manufacturers, maintenance plants and airlines and other related departments, and they are also key indicators to measure the level of engine manufacturing. However, as the most important core component of the aircraft, the stability of the aero-engine is difficult to control due to many factors such as its complex structure, hig...

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/20G06F2119/04
Inventor 刘红梅李连峰吕琛马剑
Owner BEIHANG UNIV
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