抽吸角度对高负荷、跨音速叶表附面层抽吸效应研究  

Exploring a Better Scheme of Boundary Layer Suction (BLS) Holes to Improve the Performance of a High Load Transonic Compressor Cascade

作　　者：王掩刚[1] 赵龙波[1] 任思源[1] 国瑞[1] 

机构地区：[1]西北工业大学动力与能源学院,陕西西安710072

出　　处：《西北工业大学学报》2010年第5期643-648,共6页Journal of Northwestern Polytechnical University

基　　金：国家自然科学基金(50806061);西北工业大学翱翔之星计划资助

摘　　要：以某跨音速高负荷压气机叶栅为研究对象,在其吸力面激波投射点下游40%弦长处设计了3种形式的抽吸孔,即顺流45°、逆流45°和垂直抽吸孔。应用数值模拟手段探索其来流超音速时合理的抽吸孔形式和抽吸方案,获取不同抽吸方案时叶栅性能以及流场细节,寻求叶栅性能与抽吸参数的最佳匹配。结果表明在该位置进行抽吸时,抽吸量是决定叶栅性能的主要参数,3种抽吸孔都表现为:①在抽吸量从0.1%到1.2%主流流量的增加过程中,相对于0.1%抽吸工况,叶栅出口马赫数降低17.5%、总压恢复系数提高5.5%、静压升提高8.6%、叶片负荷降低7.5%,但抽吸孔之前负荷增加,叶片负荷前移;②抽吸使得叶片表面激波投射点向下游飘移,激波强度略有增加,但使得其后附面层分离减弱,降低了叶栅损失;③抽吸使得叶栅出口流动更为均匀,尾迹亏损区减小。计算结果还显示3种孔表现出不同的抽吸性能,具体表现为:①随着抽吸量增加,其流量系数增加,但相同抽吸量时逆流45°抽吸孔流量系数始终大于顺流45°以及垂直孔;②顺流条件下,在抽吸孔入口的背风区形成较强漩涡,增加了孔内流动损失,降低了孔的有效流通面积;③随着抽吸角度从顺流45°向逆流45°变化,抽吸孔入口背风区漩涡逐渐消失,增强了其流通能力,降低了孔内流动损失。Our exploration work was done by numerical simulation of a certain such cascade;the major portion of the core of our numerical simulation is its results,which consist of two parts.The first part shows that the mass flow rate of the three schemes of suction holes is the key parameter which determines the cascade performance,and the common performances of the three schemes of suction holes are： ① when the mass flow rate of suction increases from 0.1% to 1.2% of the mainstream,the exit Mach number of cascade reduces by 17.5%,the total pressure recovery coefficient increases by 5.5%,static pressure increases by 8.6%,and blade load reduces by 7.5%,compared with the condition of 0.1% suction flow rate;but the load before the suction hole increases and the blade load moves forward;② BLS makes the shockwave projection point drift to the downstream and increases the strength of the shockwave,but it reduces the separation of boundary layer and the cascade loss;③ the flow parameter at cascade exit is more uniform after BLS,so that the area of deficit wake is reduced.The second part shows the different performances of the three schemes of suction holes： ① the discharge coefficient increases with the suction mass flow rate;under the same suction mass flow rate,the discharge coefficient of upstream 45 ° suction hole is always greater than the other two schemes;② in the downstream condition,strong vortex appears at the side of the suction hole,which increases the loss of suction flow and reduces the effective flow area of the suction hole;③ when the angle of suction hole changes from the downstream 45°to upstream 45°,the vortex disappears gradually,therefore the flow loss in the hole is reduced.The above two parts of three results each are,we believe,of some help in the designer＇s perennial strive for a good scheme of BLS holes to improve the performance of a high load transonic compressor cascade.

关 键 词：附面层 分离 附面层抽吸 抽吸孔 

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]