基于壁面静压的发动机进口总压畸变重构  

Reconstruction of engine inlet total pressure distortion based on wall static pressure

作　　者：刘旭[1] LIU Xu(Chinese Flight Test Establishment,Aviation Industry Corporation of China,Limited,Xi’an 710089,China)

机构地区：[1]中国航空工业集团有限公司中国飞行试验研究院,西安710089

出　　处：《航空动力学报》2023年第6期1360-1366,共7页Journal of Aerospace Power

摘　　要：为了满足航空发动机畸变容限控制技术对发动机进气畸变解算的要求,根据插板扰流畸变模拟试验测得的稳、动态总压和静压数据,采用神经网络方法开展了基于壁面静压的发动机进口稳态总压流场和稳态周向畸变指数重构以及动态总压紊流度重构研究。结果表明:采用神经网络方法,可以较好地建立壁面稳态静压与流场稳态总压分布的相关关系,实现通过有限壁面静压测量数据重构稳态总压流场,重构流场高、低压区范围、总压数值以及稳态周向畸变指数与测量流场吻合良好;通过在神经网络输入参数中增加中心总压以及增加壁面稳态静压测点数量可以提高稳态总压流场的重构精度;根据壁面动态静压的紊流度和气流马赫数采用神经网络方法可以直接重构获得动态总压的紊流度,重构误差在±0.25%以内。In order to establish an aero-engine inlet total pressure distortion estimation method for the application of engine distortion tolerance control,using the measured steady and dynamic pressure data of inlet distortion flow field simulating test,a study of reconstructing steady total pressure distribution and steady-state circumferential distortion index and dynamic total pressure turbulence based on steady and dynamic wall static pressures by using neural network method was conducted.The result showed that the steady total pressure distribution could be well related to the wall steady static pressure by neural network model,so that the steady total pressure flow field could be reconstructed from wall steady static pressure,the high and low pressure extent and steady-state circumferential distortion index of reconstructed total pressure field were very close to those of measured flow field.Adding center total pressure and more wall steady static pressure probes data into the neural network inputs could improve the reconstructing accuracy.The dynamic total pressure turbulence level can be reconstructed by dynamic static pressure turbulence and airflow Mach number,with the reconstruction error within ±0.25%.

关 键 词：神经网络 壁面静压 总压畸变 紊流度 流场畸变重构 

分 类 号：V235.1[航空宇航科学与技术—航空宇航推进理论与工程]