高负荷风扇气动设计——转子叶尖参数选取分析  

Aerodynamic design of highly loaded fan——Analysis of rotor tip parameter selection

作　　者：赵斌[1] 徐朋飞[1] 刘宝杰[1] 

机构地区：[1]北京航空航天大学能源与动力工程学院航空发动机气动热力科技重点实验室,北京100191

出　　处：《航空动力学报》2010年第11期2564-2570,共7页Journal of Aerospace Power

摘　　要：利用叶尖基元模型计算分析了高负荷风扇转子叶尖的关键气动设计参数,重点考察了进口轴向马赫数、激波前马赫数在不同切线速度下对基元等熵效率和总压比的影响.在Schreiber的跨声叶栅试验结果的基础上,拟合了正激波损失占基元整体损失的比例关系,用于修正模型计算得到的结果.用修正后的基元等熵效率为约束,进一步分析了转子叶尖激波前马赫数的限制值,得到了相应的叶尖基元可用总压比.完善并提供了一种简单估算高负荷跨声风扇转子叶尖性能的方法,用于指导实际工程设计.The fundamental aerodynamic design tip parameter of highly loaded fan rotor was calculated and analyzed by rotor tip element model.Axial and pre-shock Mach numbers were studied in depth involving their impact on element isentropic efficiency and total pressure ratio under different tip velocities.Based on Schreiber＇s transonic cascade experimental result,the proportion of normal shock loss in total element loss was fitted,whereby the calculated result of tip model was modified.Under the restriction of the modified efficiency,limitative pre-shock Mach number and its corresponding available total pressure ratio were evaluated.A valid method was consummated and provided to estimate the tip performance simply as a guidance of practical engineering design for highly loaded transonic fan.

关 键 词：气动设计 高负荷风扇 叶尖基元模型 基元等熵效率 波前马赫数限制值 可用总压比 

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]