Multi-fidelity simulation of aeroengine for far-offdesign conditions using iterative coupled method based on auxiliary maps  

作　　者：Weimin DENG Yibing XU Ming NI Zuojun WEI Xiaohua GAN Guangming REN 

机构地区：[1]Department of Mechanics and Aerospace Engineering,Southern University of Science and Technology,Shenzhen 518055,China [2]Shenzhen Key Laboratory of Wide-Speed-Range and Variable-Density Continuous Wind Tunnel,Shenzhen Science and Technology Innovation Committee,Shenzhen 518000,China [3]School of Aerospace Engineering,Tsinghua University,Beijing 100084,China

出　　处：《Chinese Journal of Aeronautics》2024年第11期147-167,共21页中国航空学报（英文版）

基　　金：funded by the Science and Technology Innovation Committee Foundation of Shenzhen,China(Nos.JCYJ20200109141403840 and ZDSYS20220527171405012);the National Natural Science Foundation of China(No.52106045);the Pearl River Talent Recruitment Program,China(No.2019CX01Z084)。

摘　　要：Iterative coupled methods are widely used in multi-fidelity simulation of rotating components due to the simple implementation,which iteratively eliminates the errors between the computational fluid dynamics models and approximate characteristic maps.However,the convergence and accuracy of the iterative coupled method are trapped in characteristic maps.In particular,iterative steps increase sharply as the operation point moves away from the design point.To address these problems,this paper developed an auxiliary iterative coupled method that introduces the static-pressure-auxiliary characteristic maps and modification factor of mass flow into the component-level model.The developed auxiliary method realized the direct transfer of static pressure between the high-fidelity models and the component-level model.Multi-fidelity simulations of the throttle characteristics were carried out using both the auxiliary and traditional iterative coupled methods,and the simulation results were verified using the experimental data.Additionally,the consistency between the auxiliary and traditional iterative coupled methods was confirmed.Subsequently,multi-fidelity simulations of the speed and altitude characteristics were also conducted.The auxiliary and traditional iterative coupled methods were evaluated in terms of convergence speed and accuracy.The evaluation indicated that the auxiliary iterative coupled method significantly reduces iterative steps by approximately 50%at the near-choked state.In general,the auxiliary iterative coupled method is preferred as a development of the traditional iterative coupled method in the near-choked state,and the combined auxiliary-traditional iterative coupled method provides support for successful multi-fidelity simulation in far-off-design conditions.

关 键 词：Multi-fidelity simulation Iterative method Component-level model Turbojet engines Computational fluid dynamics 

分 类 号：V23[航空宇航科学与技术—航空宇航推进理论与工程]