吸力面附面层抽吸在三维高负荷扩压叶栅中的作用机制  

Mechanism of suction surface boundary layer suction in three-dimensional high loaded diffuser cascades

作　　者：郭爽[1,2] 陆华伟[3] 宋彦萍[4] 吴锤结[1,2] 

机构地区：[1]大连理工大学运载工程与力学学部工业装备结构分析国家重点实验室,辽宁大连116024 [2]大连理工大学航空航天学院,辽宁大连116024 [3]大连海事大学轮机学院,辽宁大连116026 [4]哈尔滨工业大学能源科学与工程学院,哈尔滨150001

出　　处：《航空动力学报》2014年第11期2529-2536,共8页Journal of Aerospace Power

基　　金：国家自然科学基金(51206013;11072053);中国博士后科学基金(2013M540223);辽宁省博士启动基金项目(20131020);中央高校基本科研业务费专项资金

摘　　要：对某矩形高负荷扩压叶栅在不同弦向位置开设全叶高抽吸槽的5组方案进行了数值研究,分析了抽吸槽弦向位置等参数对抽吸量分布规律的影响;通过叶栅实验探究了局部展向抽吸方案的效果.数值仿真的计算域包含吸附叶片内部的真空腔,边界条件按照实验条件设置.研究发现:全叶高抽吸方案的抽吸量沿展向大致呈C型分布;叶高中部和端部的主要抽吸效果都体现在叶高中部流场,端部的抽吸量对叶栅角区的回流有一定的抑制效果.抽吸量沿展向的分布规律受叶栅流道和叶片内腔流场的共同作用,因此应根据三维高负荷扩压叶栅流场的具体特性对吸力面抽吸槽/孔进行细化设计.The highly loaded diffuser compressor cascade with a full-span suction slot was numerically simulated under five different chordwise suction positions in the first step.The influences of aerodynamic parameters such as suction position on the suction flow distribution were studied in detail.Then experiments on the effects of partly-span suction flow on the performance of a three-dimensional cascade were carried out.The simulation region includs the inner cavity of the suctior blade,and the boundary conditions in simulations are setaccording to the experimental conditions.The suction flow is C-type distributed along the spanwise direction in full-span suction schemes.Both of the partly-span suction schemes mainly improve the flow field around the midspan,while the suction flow around the blade roots also suppress the back flow in the corner region.Both the three-dimensional flow field of the cascade passage and inner cavity of the aspirate blade influenced the spanwise distribution of the suction flow.Therefore it is necessary to design tailored suction slots/orifices according to the characteristics of the three-dimensional high loading diffuser compressor cascades.

关 键 词：大折转角 矩形叶栅 端壁二次流 流动控制 抽吸量分布 流动损失 

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]