两级跨声风扇气动性能的实验和数值模拟  

Experimental and numerical study on aerodynamic performance of transonic two-stage fan

作　　者：杨加寿 魏新谛 唐雨萌[2,3] 冀国锋 柳阳威[2,3] YANG Jiashou;WEI Xindi;TANG Yumeng;JI Guofeng;LIU Yangwei(Guiyang Engine Design Research Institute,Aero Engine Corporation of China,Guiyang 550081,China;School of Energy and Power Engineering,Beihang University,Beijing 100191,China;National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics,Beihang University,Beijing 100191,China;National Elite Institute of Engineering,Northwestern Polytechnical University,Xi’an 710072,China)

机构地区：[1]中国航发贵阳发动机设计研究所,贵阳550081 [2]北京航空航天大学能源与动力工程学院,北京100191 [3]北京航空航天大学航空发动机气动热力国家级重点实验室,北京100191 [4]西北工业大学国家卓越工程师学院,西安710072

出　　处：《航空动力学报》2025年第2期26-36,共11页Journal of Aerospace Power

基　　金：国家自然科学基金(52106039);中国航发集团产学研合作项目(HFZL2022CXY001,HFZL2023CXY002);北京航空航天大学博士研究生卓越学术基金。

摘　　要：对某两级跨声风扇开展了实验和数值模拟研究,该跨声风扇的两级转子均采用前掠设计,第一级静子采用常规构型,末级静子则采用串列构型。对不同转速下的特性参数进行了实验测量,采用Spalart-Allmaras(SA)湍流模型和基于螺旋度修正的SA-Helicity湍流模型,对风扇100%转速和80%转速的特性进行了定常数值模拟。结果表明:SA模型过低预测了风扇的稳定裕度,SA-Helicity模型对稳定裕度、效率和压比特性的预测精度较SA模型明显提升。风扇第二级的平均负荷高于第一级,工况向近失速点移动时,总温和总压增加的贡献也主要来自于第二级。风扇主要损失来源自转子激波引起的边界层增厚和静子端区的角区分离。特别是在近失速点,第一级静子和第二级串列静子的第一排叶片端区产生的角区分离结构是引起损失剧烈增加的主要原因。Experimental research and numerical simulation were conducted on a two-stage transonic fan.Both two rotors of the two-stage fan adopted the forward-swept design,and the last stage stator employed a tandem configuration.Experimental measurements of characteristic parameters were conducted at different rotation speeds.Then,steady numerical simulations of the fan were conducted at 100%rotation speed and 80%rotation speed using the Spalart-Allmaras(SA)turbulence model and the SA-Helicity turbulence model.Results indicated that the SA model underpredicted the stall margin,while the SA-Helicity model significantly improved the prediction accuracy of the stall margin,the efficiency,and the pressure ratio.The loading subjected by the second stage was higher than that by the first stage.The second stage primarily contributed to the increase of total temperature and pressure as the operating condition moved towards the near-stall point.The shock wave and the corner separation constituted the primary sources of loss.In the near-stall condition,a large corner separation at the first stator and the first row of the stage tandem stator was the main reason for the increase of losses.

关 键 词：跨声风扇 多级风扇/压气机 湍流模型 高负荷 气动性能 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]