Prediction method for complete machine performance decline trend of aeroengine

An aero-engine and trend forecasting technology, which is applied in engine testing, machine/structural component testing, measuring devices, etc., can solve the problems of no aero-engine overall life prediction and evaluation, no performance data on aero-engine performance degradation, etc.

Inactive Publication Date: 2013-02-13
CIVIL AVIATION FLIGHT UNIV OF CHINA
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Problems solved by technology

[0002] There are two existing patents for predicting aero-engine functions, namely "Aero-engine Hardware Damage Analysis and Life Prediction Method Based on Damage Baseline" (public number: CN102288412A) and "Physical Life Prediction of Turbine Disc Probabilistic Fault Based on Bayesian Information Update" Method” (publication number: CN102682208A), the former is a damage baseline-based method for aero-eng...

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  • Prediction method for complete machine performance decline trend of aeroengine
  • Prediction method for complete machine performance decline trend of aeroengine
  • Prediction method for complete machine performance decline trend of aeroengine

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Embodiment Construction

[0026] The present invention will be further described below in conjunction with the accompanying drawings and embodiments.

[0027] Such as figure 1 Shown, the present invention comprises the following steps:

[0028] Step 1 is to determine the typical parameters that need to be monitored by the aero-engine under different working conditions.

[0029] First of all, the parameters to be monitored should be selected. The monitored parameters should accurately reflect the health status of the engine performance, and the change trend of the monitored parameters can correspond to the relevant engine failure symptoms.

[0030] The main gas path monitoring parameters of aero-engine status monitoring are:

[0031] The fan speed N1 is the fan speed of the turbofan aeroengine. Most of the thrust of a high bypass ratio turbofan engine is generated by the bypass airflow, so the fan speed N1 is generally used to represent the thrust of the turbofan engine in engineering applications an...

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Abstract

The invention provides a prediction method for complete machine performance decline trend of an aeroengine, and the prediction method comprises the steps of: firstly determining typical parameters required to be monitored of the aeroengine under different working conditions, carrying out preprocessing and similarity transformation, then amending the discharge temperature of the aeroengine, and finally calculating the discharge temperature margin, wherein the engine is needed to be returned to the factory for overhaul when the discharge temperature margin is 0. By adopting the method, key parameter data of the engine can be collected by utilizing data collecting hardware conditions equipped on an existing plane, and the engine performance change trend is predicted on the basis of the data, so that the available resources are sufficiently utilized, and the support is provided for the safety of the aeroengine.

Description

technical field [0001] The invention relates to the field of aero-engine health management, and relates to a method for predicting the decline trend of aero-engine performance by analyzing the variation trend of aero-engine parameters. Background technique [0002] There are two existing patents for predicting aero-engine functions, namely "Aero-engine Hardware Damage Analysis and Life Prediction Method Based on Damage Baseline" (public number: CN102288412A) and "Physical Life Prediction of Turbine Disc Probabilistic Fault Based on Bayesian Information Update" Method” (publication number: CN102682208A), the former is a damage baseline-based method for aero-engine hardware damage analysis and life prediction, and the latter is a method for predicting the physical life of aero-engine wheel probabilistic failures, both of which have limitations in engine life prediction However, none of them have predicted and evaluated the overall life of the most important aero-engine, nor ha...

Claims

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Application Information

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IPC IPC(8): G01M15/00
Inventor 傅强王强彭凯尚永锋李勇阎锋陈明强
Owner CIVIL AVIATION FLIGHT UNIV OF CHINA
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