Research on a high-precision real-time improvement method for aero-engine component-level model

Qiangang Zheng; Liangliang Li; Haibo Zhang; Jiajie Chen

doi:10.1515/tjj-2023-0022

Article

Research on a high-precision real-time improvement method for aero-engine component-level model

Qiangang Zheng , Liangliang Li , Haibo Zhang and Jiajie Chen

Published/Copyright: May 29, 2023

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From the journal International Journal of Turbo & Jet-Engines Volume 41 Issue 2

Abstract

In order to improve the real-time performance of the aero-engine Component-Level Model (CLM) while ensuring accuracy, a method for the Calculation of Thermodynamic Parameters of Working Fluids (CTPWF) based on a Neural Network and Newton Raphson (NN-NR) is proposed. In this method, the enthalpy or entropy under different fuel-air ratio and humidity conditions is mapped to temperature by a neural network, and the mapping output is used as the initial solution of Newton Raphson (NR) iteration. Then, a high-precision solution can be obtained through a few iterations, which avoids the shortcoming that the traditional method uses a fixed initial solution that leads to too many iterative steps. This effectively reduces the number of iterative steps and improves the calculation efficiency. This method is applied to the aero-thermodynamic calculation of each component of an engine CLM, which improves the accuracy and real-time performance of the CLM. The simulation results show that, compared to the traditional method, the proposed method improves the accuracy of the CTPWF and can reduces the single aero-thermodynamic calculation time by 25 % when humidity is not considered and by 47 % when humidity is considered. This effectively improves the real-time performance of the CLM.

Keywords: aero-engine component-level model; calculation of aero-thermodynamic; calculation of thermodynamic parameters of working fluids; real-time performance

Corresponding author: Qiangang Zheng, JiangSu Province Key Laboratory of Aerospace Power System, Nanjing University of Aeronautics and Astronautics, NO. 29 Yudao Street, Nanjing 210016, China, E-mail: zhqg@nuaa.edu.cn

Funding source: National Science and Technology Major Project of China

Award Identifier / Grant number: J2019-II-0009-0053

Award Identifier / Grant number: J2019-I-0020-0019

Award Identifier / Grant number: J2019-III-0014-0058

Funding source: Innovation Centre for Advanced Aviation Power , China

Award Identifier / Grant number: HKCX2020-02-022

Award Identifier / Grant number: HKCX2022-01-026-03

Funding source: The Fund of Prospective Layout of Scientific Research for NUAA(Nanjing University of Aeronautics and Astronautics), China

Award Identifier / Grant number: ILA220341A22

Award Identifier / Grant number: ILA220371A22

Funding source: Project funded by China Postdoctoral Science Foundation, China

Award Identifier / Grant number: 2021M701692

Funding source: Jiangsu Funding Program for Excellent Postdoctoral Talent, China

Award Identifier / Grant number: 2022ZB202

Research funding: None declared.
Conflict of interest statement: The authors declare no conflicts of interest regarding this article.
Author contributions: All the authors have accepted responsibility for the entire content of this submitted manuscript and approved submission.

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Received: 2023-03-08

Accepted: 2023-05-12

Published Online: 2023-05-29

Published in Print: 2024-05-27

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Articles in the same Issue

https://doi.org/10.1515/tjj-2023-0022

Keywords for this article

aero-engine component-level model; calculation of aero-thermodynamic; calculation of thermodynamic parameters of working fluids; real-time performance