Prediction of turboshaft engine acceleration process performance parameters based on BSO-ELM

被引:0
|
作者
Dong Q. [1 ,2 ]
Li B. [2 ]
Yan S. [2 ]
Qian R. [2 ]
机构
[1] Military Representative Office of Naval Equipment Department in Suzhou Area, Suzhou
[2] College of Aviation Foundation, Naval Aviation University, Yantai
关键词
Acceleration process; Brain storm optimization; Extreme learning machine; Model identification; Performance parameters prediction; Turboshaft engine;
D O I
10.12305/j.issn.1001-506X.2021.08.20
中图分类号
学科分类号
摘要
It is the basis of engine performance optimization and real-time monitoring to establish the prediction model of aeroengine performance parameters which can meet the requirements of both accuracy and real-time. Extreme learning machine (ELM) has good adaptability to the complex nonlinear aeroengine system. In this paper, a brain storm optimization (BSO) algorithm is proposed to optimize the network parameters of ELM for improving its performance. The acceleration process data of the engine on the bench test are used as training and verification samples, and the performance parameter prediction model of the turboshaft engine acceleration process is obtained by regression identification using BSO-ELM algorithm. The results show that the prediction parameters of output parameter gas generator speed ng, gas generator outlet temperature T4 and pressure ratio πc are better than the prediction models obtained by backpropagation neural network optimized with BSO algorithm and ELM method optimized with particle swarm optimization, which indicates the feasibility and superiority of the BSO-ELM prediction model. In the same simulation environment, the BSO-ELM algorithm can greatly improve the computational efficiency and improve the real-time performance of the prediction model. © 2021, Editorial Office of Systems Engineering and Electronics. All right reserved.
引用
收藏
页码:2181 / 2188
页数:7
相关论文
共 32 条
  • [1] LIAN X C, WU H., Principle of aero engine, (2005)
  • [2] HAN W J, LI J R, WANG J, Et al., Design method of fuel supply law for turbofan engien acceleration bsaed on a real-time model, Aeroenign, 41, 2, pp. 5-9, (2015)
  • [3] ASGARI H, VENTURINI M, CHEN X Q, Et al., Modeling and simulation of the transient behavior of an industrial power plant gas turbine, Journal of Engineering for Gas Turbines and Power, 136, 6, (2014)
  • [4] ZHENG F H., Aeroengine modeling research based on system identification, (2018)
  • [5] YU B, SHU W J, CAO C., A novel modeling method for aircraft engine using nonlinear autoregressive exogenous (NARX) models based on wavelet neural networks, International Journal of Turbo & Jet-Engines, 35, 2, pp. 161-169, (2018)
  • [6] ASGARI H, CHEN X Q, MENHAJ M B, Et al., Artificial neural network-based system identification for a single-shaft gas turbine, Journal of Engineering for Gas Turbines and Power, 135, 9, pp. 169-175, (2013)
  • [7] WANG G C, YANG C, XU B, Et al., Engine start identification based on parameter optimization of improved PSO-SVM, Gas Turbine Experiment and Research, 24, 1, pp. 35-41, (2011)
  • [8] ZHOU D, ZHUANG X, ZUO H F, Et al., Hazard identification and prediction system for aircraft electrical system based on SRA and SVM, Proceedings of the Institution of Mechanical Engineers, 234, 4, pp. 1014-1026, (2020)
  • [9] BERGHOUT T, MOUSS L H, KADRI O, Et al., Aircraft engines remaining useful life prediction with an improved online sequential extreme learning machine, Applied Sciences, 10, 3, (2020)
  • [10] ZHANG S S, LEI D., A dynamic ensemble extreme learning machine model for aircraft engine health condition prediction, Journal of Aerospace Power, 29, 9, pp. 2085-2090, (2014)