A new method to improve the real-time performance of aero-engine component level model
-
Changpeng Cai
Abstract
In order to improve the real-time performance of aero-engine component-level models, an automatic fast positioning interpolation method is proposed. Based on the maximum parameter slope, this method can automatically determine the interpolation cut in point, change the disadvantage of low efficiency of traditional sequential interpolation from the starting point, effectively reduce the interpolation interval, thus greatly improving the efficiency of interpolation. The method is applied to the calculation of gas thermodynamic parameters and the interpolation of the characteristic of rotating parts ,so as to ameliorate the real-time performance of the single-stage flow path calculation of the component-level model. Simulation results show that, compared with the traditional method, the method proposed in this paper improves the fan characteristic calculation efficiency by 47.5%, reduces the time of single complete flow calculation by 74.3% when the dynamic and steady-state accuracy changes are less than 0.4%, which greatly improves the real-time performance of the component-level model.
Funding source: National Science and Technology Major Project
Award Identifier / Grant number: 2017-V-0004-0054
-
Author contribution: All the authors have accepted responsibility for the entire content of this submitted manuscript and approved submission.
-
Research funding: This study was supported in part by National Science and Technology Major Project under Grant 2017-V-0004-0054.
-
Conflict of interest statement: The authors declare no conflicts of interest regarding this article.
References
1. Jaw, LC, Mattingly, JD. Aircraft engine controls: design, system analysis, and health monitoring. Reston, VA: American Institute of Aeronautics and Astronautics; 2009:15–40 pp.10.2514/4.867057Search in Google Scholar
2. Jaw, LC, Garg, S. Propulsion control technology development in the United States: a historical perspective. Ohio, USA: Glenn Research Center; 2005, NASA/TM-2005-213978.Search in Google Scholar
3. JianGuo, S. Prospects of the aeroengine control development in the early time of the 21st century. J Aerosp Power 2001;16:97–102. https://doi.org/10.13224/j.cnki.jasp.2001.02.001.Search in Google Scholar
4. Zhang, S. A review of aeroengine control system. J Aerosp Power 2004;03:88–95. https://doi.org/10.13224/j.cnki.jasp.2004.03.018.Search in Google Scholar
5. Zheng, Q, Du, Z, Fu, D, Hu, Z, Zhang, H. Direct thrust inverse control of aero-engine based on deep neural network. Int J Turbo Jet Engines 2021;38:391–6. https://doi.org/10.1515/tjj-2018-0049.Search in Google Scholar
6. Simon, DL. An integrated architecture for on-board aero-engine performance trend monitoring and gas path fault diagnostics. Ohio, USA: Glenn Research Center; 2010, NASA/TM-2010-216358.Search in Google Scholar
7. Volponi, AJ. Gas turbine engine health management: past, present and future trends[J]. J Eng Gas Turbines Power 2014;136:051201. https://doi.org/10.1115/1.4026126.10.1115/GT2013-96026Search in Google Scholar
8. Meher-Homji, CB, Mistree, F, Karandikar, S. An approach for the integration of condition monitoring and multiobjective optimization for gas turbine maintenance management. Int J Turbo Jet Engines 1994;11:43–52. https://doi.org/10.1515/tjj.1994.11.1.43.Search in Google Scholar
9. Zheng, Q. Research on integrated optimization control of intelligent aero-engine. Nanjing: Nanjing University of Aeronautics and Astronautics; 2018.Search in Google Scholar
10. Sanghi, V, Sane, SK. Digital simulation of propulsion system performance for cycle optimization studies. Int J Turbo Jet Engines 1999;16:27–37. https://doi.org/10.1515/tjj.1999.16.1.27.Search in Google Scholar
11. Liu, X, Zhang, W, Huang, Y. Research methods and development of analytical redundancy technology. Comput Meas Control 2005;07:710–17. https://doi.org/10.16526/j.cnki.11-4762/tp.2005.07.032.Search in Google Scholar
12. Loboda, I, Feldshteyn, Y, Yepifanov, S. Gas turbine diagnostics under variable operating conditions. Int J Turbo Jet Engines 2007;24:231–44. https://doi.org/10.1515/tjj.2007.24.3-4.231.Search in Google Scholar
13. Reberga, L, Henrion, D, Bernussou, J, Vary, F. LPV modeling of a turbofan engine. IFAC Proc Vol 2005;38:526–31. https://doi.org/10.3182/20050703-6-cz-1902.00488.Search in Google Scholar
14. Gilbert, W, Henrion, D, Bernussou, J, Boyer, D. Polynomial LPV synthesis applied to turbofan engines. Control Eng Pract 2010;18:1077–83. https://doi.org/10.1016/j.conengprac.2008.10.019.Search in Google Scholar
15. Yang, X. Research on performance recovery control method for aero-engine. Nanjing: Nanjing University of Aeronautics and Astronautics; 2019.Search in Google Scholar
16. Zhao, H. Research on nonlinear control for aeroengines based on equilibrium manifold expansion model. Harbin: Harbin Institute of Technology; 2011.Search in Google Scholar
17. Tang, S, Tong, W. Turbofan engine transient modeling based on inter-component volume method. J Aerosp Power 2013;03:234–8. https://doi.org/10.13224/j.cnki.jasp.2013.03.032.Search in Google Scholar
18. Kopasakis, G, Connolly, JW, Seidel, J. Propulsion system dynamic modeling of the NASA supersonic concept vehicle for AeroPropulsoServoElasticity. Cleveland, Ohio: NASA Glenn Research Center; 50th AIAA/ASMW/SAE/ASEE Joint Propulsion Conference. 2014:3684–99 pp.10.2514/6.2014-3684Search in Google Scholar
19. Roberts, RA, Eastbourn, SM. Modeling techniques for a computational efficient dynamic turbofan engine model. Int J Aerosp Eng 2014;2014:283479. https://doi.org/10.1155/2014/283479.Search in Google Scholar
20. Pan, M, Chen, L, Zhou, Y. A multi-dynamics approach to turbofan engine modeling. Chinese J Aeronaut 2019;40:99–110. https://doi.org/10.7527/S1000-6893.2018.22632.Search in Google Scholar
21. Broyden, CG. A class of methods for solving nonlinear simultaneous equations. Math Comput 1965;19:577–93. https://doi.org/10.1090/s0025-5718-1965-0198670-6.Search in Google Scholar
22. Huang, X, Wang, Z, Zhang, X. Research of a corrected Broyden’s method on the aero-engine performance simulation. Sci Technol Eng 2012;21:103–14.Search in Google Scholar
23. Dhamacharoen, A. An efficient hybrid method for solving systems of nonlinear equations. J Comput Appl Math 2014;263:59–68. https://doi.org/10.1016/j.cam.2013.12.006.Search in Google Scholar
24. Al-Towaiq, MH, Abu Hour, YS. Two improved Methods Based on Broyden’s Newton Methods for the solution of nonlinear system equations. J Eng Appl Sci 2016;11:2344–8. https://doi.org/10.36478/jeasci.2016.2344.2348.Search in Google Scholar
25. Wang, Y, Li, Q. Numerical calculation of aero-engine model based on self-tuning Broyden Quasi-Newton method. J Aerosp Power 2016;1:249–56. https://doi.org/10.13224/j.cnki.jasp.2016.01.032.Search in Google Scholar
26. Henrique, GJ, Cleverson, B, Roberto, BJ, Tomita, JT. Real-time gas turbine model for performance simulations. J Aerosp Technol Manag 2017;9:346–56. https://doi.org/10.5028/jatm.v9i3.693.Search in Google Scholar
27. Wu, Q, Li, Q. Research on method for solving aero-engine thermodynamic system model. Comput Integr Manuf Syst 2019;36:83–8.Search in Google Scholar
28. Pang, S. Construction method of aeroengine component-level model based on precise partial derivative. China, Nanjing: China National Intellectual Property Administration 2020;CN108733906A.Search in Google Scholar
29. Xiao, W. The research on real-time modeling and simulation for a turbine-fan aeroengine. Nanjing: Nanjing University of Aeronautics and Astronautics; 2008.Search in Google Scholar
30. Yin, K, Zhou, W. Research on methods of improving real-time performance for aero-engine component-level model. J Propuls Technol 2017;01:205–12. https://doi.org/10.13675/j.cnki.tjjs.2017.01.026.Search in Google Scholar
31. Qiao, K. Research on sensor signal reconstruction technology for turbofan engine control system. Nanjing: Nanjing University of Aeronautics and Astronautics; 2015.Search in Google Scholar
© 2020 Walter de Gruyter GmbH, Berlin/Boston
Articles in the same Issue
- Frontmatter
- Integration of a transonic high-pressure turbine with a rotating detonation combustor and a diffuser
- Prediction of compressor nominal characteristics of a turboprop engine using artificial neural networks for build standard assessment
- Study on inversion control for integrated helicopter/engine system with variable rotor speed based on state variable model
- Effects of casing angle on the performance of parallel hub axial annular diffuser
- Experimental research on the performance of the forward variable area bypass injector for variable cycle engines
- Film cooling characteristics on a grooved surface with different injection orientation angles
- Aero-thermal optimization of the rim seal cavity to enhance rotor platform thermal protection
- Numerical study of the parameters of a gas turbine combustion chamber with steam injection operating on distillate fuel
- An active fault-tolerant control strategy of aircraft engines based on multi-model predictive control
- Conjugate heat transfer analysis of a radially cooled nozzle guide vane in an aero gas turbine engine
- A new method to improve the real-time performance of aero-engine component level model
- Experimental and numerical investigation of expansion corner effects on isolator performance
Articles in the same Issue
- Frontmatter
- Integration of a transonic high-pressure turbine with a rotating detonation combustor and a diffuser
- Prediction of compressor nominal characteristics of a turboprop engine using artificial neural networks for build standard assessment
- Study on inversion control for integrated helicopter/engine system with variable rotor speed based on state variable model
- Effects of casing angle on the performance of parallel hub axial annular diffuser
- Experimental research on the performance of the forward variable area bypass injector for variable cycle engines
- Film cooling characteristics on a grooved surface with different injection orientation angles
- Aero-thermal optimization of the rim seal cavity to enhance rotor platform thermal protection
- Numerical study of the parameters of a gas turbine combustion chamber with steam injection operating on distillate fuel
- An active fault-tolerant control strategy of aircraft engines based on multi-model predictive control
- Conjugate heat transfer analysis of a radially cooled nozzle guide vane in an aero gas turbine engine
- A new method to improve the real-time performance of aero-engine component level model
- Experimental and numerical investigation of expansion corner effects on isolator performance
