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采用数值模拟方法研究了一系列弯高和不同弯角的叶片周向弯曲造型设计对NASA Rotor37跨声速压气机转子的气动性能的影响。结果表明:动叶弯曲能够有效地提高压气机的稳定裕度和效率,且裕度的增量与弯高和弯角呈“双峰”关系。动叶的周向弯曲能够引起叶顶低能流体向主流区迁移,从而降低叶顶区域的流动损失,但在主流区流动损失有所增加,并且叶片通道内流体的质量流量沿叶高方向被重新分配。
A series of numerical simulation methods were used to study the influence of a series of buckling and corner bending blade design on aerodynamic performance of transonic compressor rotor of NASA Rotor37. The results show that the buckling of buckets can effectively improve the stability margin and efficiency of the compressor, and the increment of margin is related to the curve height and corner angle. Circumferential buckling of buckets can cause the low-energy fluid at the tip to migrate toward the mainstream and reduce the loss of flow in the top of the lobe, but the flow loss increases in the mainstream and the mass flow of the fluid in the vane is re-oriented in the leaf height distribution.