轮毂局部修型对轴流压气机转子叶根角区分离的抑制机理研究  

The Inhibition Mechanism of Local Modification of Hub Curve on Root Corner Separation of Axial Compressor Rotor

作　　者：姚飞 刘玉强 李宗明 王颖[2] 崔伟伟 王翠苹 杨来顺 岳光溪 YAO Fei;LIU Yuqiang;LI Zongming;WANG Ying;CUI Weiwei;WANG Cuiping;YANG Laishun;YUE Guangxi(College of Civil Engineering and Architecture Shandong University of Science and Technology,Qingdao 266590,China;College of Architecture Engineering Weifang University of Science and Technology,Weifang 262700,China;Clean Energy Laboratory,Shandong University of Science and Technology,Qingdao 266590,China)

机构地区：[1]山东科技大学土木工程与建筑学院,青岛266590 [2]潍坊科技学院建筑工程学院,潍坊262700 [3]山东科技大学清洁能源实验室,青岛266590

出　　处：《工程热物理学报》2022年第12期3235-3243,共9页Journal of Engineering Thermophysics

基　　金：国家自然科学基金面上项目(No.52076124);山东省自然科学基金面上项目(No.ZR2020ME173)。

摘　　要：针对NASA的Rotor67转子,采用数值方法详细研究了叶根尾缘点附近轮毂型线局部曲率调整对压气机总体性能和叶根角区分离结构的影响。在不改变叶根基元级叶型的前提下,通过改变转子叶根尾缘点附近10%弦长范围内对应的轮毂型线局部倾斜角,设计了五种具有不同几何分布特征的轮毂型线方案。结果表明,叶根尾缘附近轮毂型线曲率的局部调整对转子20%叶高以下的三维流场具有明显影响,但是对中径和叶尖流场的影响相对较小。随着叶根尾缘点附近轮毂型线倾斜角的增加,转子叶根的气动载荷逐渐前移,对应尾缘附近叶片通道内的横向静压差减小,进而减小了低能流体向吸力面侧轮毂角区的输运和堆积效应。叶根尾缘点附近轮毂型线倾斜角的增加所导致的该区域亚声速气流的局部加速效应,一方面对该区域的分离结构有显著的压制效果,另一方面有效缓解了叶根尾缘附近的沿程静压增加量。综合作用下,压气机转子叶根尾缘点附近的轮毂型线局部调整,使得叶根角区存在的大范围分离现象得到有效抑制和消除,并实现了压气机转子设计点等熵效率和增压比分别较原型方案提升了0.41%和0.71%以上。The effects of local geometrical adjustment of hub curve near the trailing edge of blade root on the overall performance and the separation structure near hub corner of NASA rotor67 were studied numerically.Five types of hub curves were designed by changing the inclined angle near the trailing edge point of blade root,with the shape of the element of blade root unchanged.The numerical results show that the local adjustment of hub curve near the trailing edge of blade root has an obvious effect on the three-dimensional flowfield below 20%span of rotor blade from hub,while it has less effect on the flow in other region.With increase of the local inclined angle of hub curve near trailing edge,the aerodynamic load of element near blade root moves forward,and the transverse static pressure difference in passage near trailing edge decreases accordingly,which benefits to reduce the transporting and accumulation of low-energy fluid in the hub corner near suction side of rotor blade.It’s noted the local flow acceleration induced by the increase of inclined angle near trailing edge of blade root,performs well in attenuation of the corner separation,and reduces the increase magnitude of static pressure near trailing edge of blade root in some extent.Therefore,with the comprehensive effects of local hub curve adjustment near trailing edge of blade root,the flow characteristic near blade root has improved significantly,and both the isentropic efficiency and total pressure ratio of transonic rotor have increased over 0.41% and 0.71%respectively.

关 键 词：轮毂型线局部调整 横向压力梯度 气动载荷 角区分离 低能流体 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]