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Aeroengine transition state key performance parameter prediction method

A key performance parameter, aero-engine technology, applied in the field of aero-engine performance parameter prediction, which can solve the problems of complex calculation, difficult model selection, non-convergence of iterations, etc.

Active Publication Date: 2018-08-07
DALIAN UNIV OF TECH
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  • Description
  • Claims
  • Application Information

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Problems solved by technology

Among them, the model-based method is complex to calculate, and there may be problems such as iterative non-convergence during real-time calculation; the statistical-based method is mainly for statistical analysis of engine failures, maintenance records, etc.; the regression-based method sometimes does not necessarily have obvious differences between variables. Linear or other functional relationships, the model is difficult to choose

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  • Aeroengine transition state key performance parameter prediction method
  • Aeroengine transition state key performance parameter prediction method
  • Aeroengine transition state key performance parameter prediction method

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Embodiment Construction

[0084] The specific implementation manners of the present invention will be further described below in conjunction with the accompanying drawings and technical solutions.

[0085] The data used are 180 sets of transition state bench test data of a certain type of aero-engine provided by a domestic research institute.

[0086] The first step is to preprocess the performance parameter data of the aircraft

[0087] (1) Data categories mainly include throttle lever angle PLA, low pressure rotor speed n 1 , high pressure rotor speed n 2 , ambient pressure p 0 , High pressure compressor outlet pressure p 31 , oil pressure p f , compressor outlet temperature t 1 , exhaust gas temperature EGT, lead angle α 2 , a total of 9 groups of parameters.

[0088] (2) Data integration: Combine data from multiple data sources (such as excel, txt) and store them in a unified manner to establish a data warehouse for aircraft performance parameters.

[0089] (3) Resampling: analyze the colle...

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Abstract

The invention belongs to the aeroengine performance parameter prediction technical field, and provides an Aeroengine transition state key performance parameter prediction method comprising the following steps: using Aeroengine transition state stand test data provided by certain institute to build a training data set and a test data set; using parameter combination to predict and analyze an exhaust temperature via an information fusion idea; using a mobile window technology to carry out rolling learning, thus predicting engine low pressure rotor rotating speed and exhaust temperature parameters from the engineering practical application angle.

Description

technical field [0001] The invention belongs to the technical field of aero-engine performance parameter prediction, and in particular relates to a method for predicting key performance parameters of an aero-engine transition state. Background technique [0002] As the core component of an aircraft, an aero-engine's operating status directly determines the stability and safety of the entire aircraft. While the performance of aero-engines has been greatly improved, the structure has become more complex, and condition monitoring and maintenance have become increasingly difficult. Among them, the transition state performance of the engine is directly related to the performance of the aircraft's take-off, acceleration flight, and maneuvering flight. Therefore, the requirements for the rapidity, stability, safety and reliability of the aero-engine transition state are extremely high. The performance parameters of the engine can reflect the health status of the engine. Therefore,...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M15/00B64F5/60
CPCB64F5/60G01M15/00
Inventor 张硕李济邦孙希明刘敏
Owner DALIAN UNIV OF TECH