Numerical simulation research on multiphase flow of aviation centrifugal pump based on OpenFOAM  

作　　者：Xianwei LIU Jiangfeng FU Junjie YANG Dewen YIN Zhenhua ZHOU Huacong LI 

机构地区：[1]College of Power and Energy,Northwestern Polytechnical University,Xi’an 710072,China [2]Norinco Group Testing and Research Institute,Huayin 714200,China [3]AECC Xi’an Engine Control Technology Co.Ltd.,Xi’an 710077,China [4]AECC Guizhou Honglin Aero Engine Control Technology Co.Ltd.,Guiyang 550009,China

出　　处：《Chinese Journal of Aeronautics》2024年第4期256-275,共20页中国航空学报（英文版）

基　　金：supported by the National Science and Technology Major Project, China (No. J2019-V-0016-0111);the Aviation Engine and Gas Turbine Basic Science Center Project, China (No. P2022-B-V-003-001);the Defense Industrial Technology Development Program, China (No. JCKY2022607C002);the AECC Industry University Cooperation Project, China (No. HFZL2022CXY013);the National Natural Science Foundation of China (No. 52372396);the Key R&D Project in Shaanxi Province, China (No. 2021GXLH-01-16)。

摘　　要：This paper aims to tackle the calculation efficiency problem raised in the cavitation-flow simulation of the aviation centrifugal pump due to the fading-away interface resulting from the dissipation of numerics used in the phase-change control equation for unstructured-grid multiphase flow,and due to the limitation of flow time-step in whole flow regimes,the control equation of vapor–liquid two-phase flow considering cavitation mass transport is established firstly,modifying the momentum equation by introducing the surface tension,and adding the artificial convective flow to the phase equation to solve the numerical dissipation problem.Secondly,in consideration of the local time step principle and based on the multi-dimensional general limiter algorithm with explicit solutions under the OpenFOAM platform,a solution method of steady-state VOF (Volume of Fluid) model considering cavitation two-phase change is constructed,and the feasibility of this method is verified by NACA hydrofoil and NASA flat plate inducer.Finally,based on the platform developed,the cavitation performance of an aviation centrifugal pump inducer is analyzed.The research results show that the error of the calculated cavitation pressure distribution for NACA hydrofoil between the simulation test and the experimental-test is less than 5%,and the maximum error of calculated cavitation number at pump head dropping for NASA high-speed flat plate inducer between the simulation test and the experimental-test is 2.1%.The cavitation area observed in the simulation test is the same as that obtained in the high-speed photography test.Based on the OpenFOAM simulation method,the position of pump head dropping of the fuel centrifugal pump can be accurately captured.The error of the calculated cavitation number at pump head dropping between the simulation test and the experimental test is about 3.7%,showing high calculation accuracy.

关 键 词：Aero engine Fuel centrifugal pump Multiphase flow OPENFOAM Volume of fluid 

分 类 号：V233.2[航空宇航科学与技术—航空宇航推进理论与工程]