A modified streamwise body force model of fan with distorted inflow for rapid propulsion-airframe integrated simulation  

作　　者：Zhiping LI Yafei ZHANG Tianyu PAN Jian ZHANG 

机构地区：[1]National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics,Beihang University,Beijing 100191,China [2]Research Institute of Aero-Engine,Beihang University,Beijing 100191,China [3]School of Energy and Power Engineering,Beihang University,Beijing 100191,China

出　　处：《Chinese Journal of Aeronautics》2023年第12期202-213,共12页中国航空学报（英文版）

基　　金：supported by the National Natural Science Foundation of China(Nos.52176032,51976005 and 52006002);the Advanced Jet Propulsion Creativity Center,China(No.HKCX2020-02-013);the National Science and Technology Major Project,China(Nos.2017-II-0004-0016 and 2017-II-0005-0018);the Fundamental Research Funds for the Central Universities,China;the Beijing Nova Program,China。

摘　　要：Streamwise Body Force Model(SBFM)could be used to simulate the force of blade on the airflow,resulting in rapid propulsion-airframe integrated simulation.However,when subjected to inlet distortion,the upstream flow field of fan stage is redistributed,which causes inaccurate prediction of fan stage performance.As inspired by the upstream influence of compressor,this paper aims to present a modification strategy for SBFM method to predict the compressor performance under circumferential inlet distortion without any knowledge of compressor geometry.Based on the linearized motion equation,the Upstream Influence Model(UIM)is introduced to predict the upstream flow field redistribution.Then the theoretical Mach number at Aerodynamic Interface Plane(AIP)position is calculated and selected to determine the corresponding body force coefficients based on the functional relationship between body force coefficients and Mach number,thus the upstream influence of compressor could be accurately quantified and the Modified Streamwise Body Force Model(MSBFM)could be established.Two studied cases are calculated with different methods and the upstream flow fields are analyzed.The prediction error of MSBFM method for compressor adiabatic efficiency is less than 3%,and the calculation efficiency is improved 20 times under the condition of ensuring computing accuracy.The MSBFM method has the potential for rapid propulsion-airframe integrated simulation.

关 键 词：Integrated simulation Streamwisebody force model Circumferential inletdistor-tion Upstream influence model Compressorperformance 

分 类 号：V211.48[航空宇航科学与技术—航空宇航推进理论与工程] V231