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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 key aerodynamic design parameters of the rotor tip of high-load fan were calculated and analyzed by using the tip-element model, and the axial Mach number of the inlet was emphatically investigated. The isentropic efficiency and total pressure ratio under different tangent velocities Based on the results of Schreiber's transonic cascades, the proportional relationship between the loss of normal shocks and the total loss of the elementary elements is fitted and used to correct the results of the model calculation. The corrected elementary isentropic efficiency As a constraint, the limit values of the rotor Mach-Zehnder's Mach number are further analyzed and the available total pressure ratio of the tip element is obtained.The method to simply estimate the rotor blade tip's performance under high load is proposed.Furthermore, , Used to guide the actual project design.