受限空间欠采样条件下航空发动机关键截面流场重构方法研究进展  

Flow Field Reconstruction Method for Key Sections of Aeroengine Based on Undersampling in Confined Space

作　　者：徐笳森 郑培英 张轲 娄方远 XU Jia-sen;ZHENG Pei-ying;ZHANG Ke;LOU Fang-yuan(Institute for Astronautics,Nanjing University of Aeronautics and Astronautics,Nanjing 211106,China;AECC Shenyang Engine Research Institute,S henyang 110015,China;Institute for Aero Engine,Tsinghua University,Beijing 100084,China)

机构地区：[1]南京航空航天大学航天学院,南京211106 [2]中国航发沈阳发动机研究所,沈阳110015 [3]清华大学航空发动机研究院,北京100084

出　　处：《航空发动机》2023年第5期47-56,共10页Aeroengine

基　　金：航空动力基础研究项目资助。

摘　　要：由于受整机环境下几何特征对探针位置的限制以及3维流动等因素影响,通过有限的测点数据准确获取整机关键测试截面参数非常困难。为解决这一难题,综合关键截面流场重构项目的研究成果,针对航空发动机内强3维、强不均匀流场,介绍了一种受限空间欠采样条件下航空发动机复杂流场重构技术。基于航空发动机内流场近周期分布的特征,利用离散的探针数据通过“多波束近似”的方法来精确重构发动机内部的周向流场。相关技术在重构多级压气机出口截面总压分布、燃烧室出口热斑分布、高压涡轮出口截面总温分布的测试中进行了初步试验验证,结果表明:重构结果与真实试验结果的误差分别小于0.1%、0.5%、0.3%。与传统均布或等节距探针布局方案及均值数据处理方法相比,采用新的探针布局方案及流场重构方法可以实现航空发动机压气机出口总压场、燃烧室及高压涡轮出口总温场的精确重构。Obtaining accurate key station parameters for gas turbine engines with limited measuring points is extremely challenging due to geometric constraints on probe position and three-dimensional flow effects under the whole engine environment.To address the issue,based on the research results of the key station flow field reconstruction project,in the context of strong three-dimensional and nonuniform flow fields inside gas turbines,an innovative technique called"flow reconstruction based on under-sampled discrete measurements in the confined gas turbine flow path"was proposed.This technique aims to accurately reconstruct the complex flow field within the engine by leveraging the approximate-periodic distribution characteristics observed in the flow.This is achieved by utilizing discrete probe data and employing a"multi-wavelet approximation"method.Preliminary experimental validation has been conducted on the reconstruction of the total pressure distribution at the exit section of a multi-stage compressor,the distribution of hot streaks at the exit of the combustor,and the total temperature field at the exit of the high-pressure turbine.The results show that the errors between the reconstructed results of the three distribution fields and the actual test results are less than 0.1%,0.5%,and 0.3%,respectively.Compared with traditional approaches such as uniform or equidistant probe layouts and averaging-based data processing methods,the new probe layout scheme and the multiwavelet approximation method enable precise reconstruction of the total pressure field at the compressor exit,as well as the total temperature field at the combustor and high-pressure turbine exits.

关 键 词：流场重构 多波束近似 多级轴流压气机 燃烧室 温度分布因子 高压涡轮 航空发动机 

分 类 号：V233.7[航空宇航科学与技术—航空宇航推进理论与工程]