几何偏差对可控扩散叶型性能影响规律及机理  

Influence of geometric variation on aerodynamic performance of controlled diffusion airfoil

作　　者：孟德君 史文斌 刘佳鑫 徐朋飞 王丁喜[1] 于贤君[3] Dejun MENG;Wenbin SHI;Jiaxin LIU;Pengfei XU;Dingxi WANG;Xianjun YU(National Elite Institute of Engineering,Northwestern Polytechnical University,Xi’an 710072,China;AECC Shenyang Engine Research Institute,Shenyang 110015,China;Research Institute of Aero-Engine,Beihang University,Beijing 102206,China;CAAC Airworthiness Certification Center,Beijing 100102,China)

机构地区：[1]西北工业大学国家卓越工程师学院,西安710072 [2]中国航发沈阳发动机研究所,沈阳110015 [3]北京航空航天大学航空发动机研究院,北京102206 [4]中国民用航空适航审定中心,北京100102

出　　处：《航空学报》2024年第19期23-33,共11页Acta Aeronautica et Astronautica Sinica

基　　金：国家级项目。

摘　　要：为了研究几何偏差对叶型性能的影响规律和机理,采用Hicks-Henne函数模化叶型轮廓度偏差、轮廓度变化率偏差,并叠加在可控扩散叶型(CDA)上,对偏差叶型进行了S1流面数值计算。计算结果表明,轮廓度变化率较小时,叶型性能随正负轮廓度偏差幅值的变化趋势是对称的,但轮廓度变化率较大时,正负轮廓度偏差均会导致叶型性能下降,正偏差的影响超过负偏差。几何偏差造成的附面层局部分离甚至提前转捩是叶型性能降低的主要原因。基于上述研究建立了CDA叶型几何偏差敏感区,敏感区域包括距离前缘5%弦长以内的叶型区域及附面层转捩点之前的吸力面区域。偏差敏感区有利于改进加工公差准则,降低压气机气动性能风险。This paper conducts research on the law and mechanism of influence of local geometric variations on airfoil performance.The Hicks-Henne function is used to model the contour variation and contour gradient variation of Controlled Diffusion Airfoil(CDA) to perform S1 stream surface numerical calculation.The calculation results indicate that the trend of variation of blade performance with positive and negative airfoil contour variation amplitude is symmetrical,when airfoil contour gradient variation is small.However,when airfoil contour gradient variation is large,both positive and negative airfoil contour variations lead to a decrease in airfoil performance,and influence of positive variations surpasses that of negative variations.Boundary layer separation and even transition in advance caused by geometric variations is the major reason for the decrease in airfoil performance.Based on the research results,the sensitive regions for CDA are established,which are within 5% chord from the leading edge and the suction surface before boundary layer transition.The variation sensitive regions are conducive to improving processing tolerance criteria and reducing the aerodynamic performance risk of compressors.

关 键 词：可控扩散叶型 轮廓度 轮廓度变化率 损失 攻角范围 

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]