Multi-fidelity simulation of aeroengine across wide operation range using auxiliary fully coupled method

Deng, Weimin1,3; Xu, Yibing2; Ni, Ming1,3; Wei, Zuojun1,3; Gan, Xiaohua1,3; Ren, Guangming1,3

2024-04-01

10.1016/j.ast.2024.109059

AEROSPACE SCIENCE AND TECHNOLOGY   影响因子和分区

1270-9638

1626-3219

Multi-fidelity simulations for the design point or equilibrium lines of aeroengines are implemented using fully coupled methods, simultaneously optimizing computational resources and speed. Fully coupled methods remove the requirement of characteristic maps by directly incorporating computational fluid dynamics models of subcomponents into the thermodynamic model of an aeroengine. However, poor convergence remains an urgent problem for fully coupled methods, particularly when performing multi-fidelity simulations in the near-boundary region. In response to this challenge, an auxiliary fully coupled method was developed in this study. This auxiliary method introduces a parametric priori knowledge and auxiliary coordinate transformations into the existing direct fully coupled method. An automated multi-fidelity simulation platform was established in-house and validated using the KJ66 turbojet engine. The simulation results of the equilibrium line were then compared with experimental data to validate the high accuracy and reliability of the multi-fidelity simulation. Moreover, two fundamental selection schemes for matching parameters (mass flow or static pressure, transferred between the computational fluid dynamics and thermodynamic models) were implemented and systematically compared. The results demonstrate that the adaptive selection of matching parameters extends the application of multifidelity simulations to a broader operation range. In addition, the auxiliary fully coupled method was applied to a multi-fidelity simulation of a wider operation range, such as an adjustable nozzle area and variable power extraction. It was also compared with the existing direct fully coupled method with respect to the stable convergence scope. For the mass-flow matching scheme, the maximum stable convergence scope of the direct method was extended from 105 % to 315 % by the auxiliary method. For the static-pressure matching scheme, the auxiliary method also broadened the maximum stable convergence scope of the direct method from 55 % to 190 %. The comparison reveals that the auxiliary fully coupled method exhibits a wider range of far-off-design conditions, including the near-boundary region.

Multi-fidelity simulation Fully coupled method A parametric priori knowledge Auxiliary coordinate transformation Aeroengine

SCI ; EI

英语

第一 ; 通讯

Science and Technology Innovation Committee Foundation of Shenzhen["JCYJ20200109141403840","ZDSYS20220527171405012"] ; National Natural Science Foundation of China (NSFC)[52106045]

Engineering

Engineering, Aerospace

WOS:001219156600001

ELSEVIER FRANCE-EDITIONS SCIENTIFIQUES MEDICALES ELSEVIER

ENGINEERING

Web of Science

1.Southern Univ Sci & Technol, Dept Mech & Aerosp Engn, Shenzhen 518055, Peoples R China
2.Tsinghua Univ, Sch Aerosp Engn, Beijing 100084, Peoples R China
3.Shenzhen Sci & Technol Innovat Comm, Shenzhen Key Lab Wide Speed Range & Variable Dens, Shenzhen 518000, Peoples R China

Deng, Weimin,Xu, Yibing,Ni, Ming,et al. Multi-fidelity simulation of aeroengine across wide operation range using auxiliary fully coupled method[J]. AEROSPACE SCIENCE AND TECHNOLOGY,2024,147.

Deng, Weimin,Xu, Yibing,Ni, Ming,Wei, Zuojun,Gan, Xiaohua,&Ren, Guangming.(2024).Multi-fidelity simulation of aeroengine across wide operation range using auxiliary fully coupled method.AEROSPACE SCIENCE AND TECHNOLOGY,147.

Deng, Weimin,et al."Multi-fidelity simulation of aeroengine across wide operation range using auxiliary fully coupled method".AEROSPACE SCIENCE AND TECHNOLOGY 147(2024).