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为优化压气机叶片前缘形状以改善叶型性能,提出了一种曲率连续叶片前缘的设计方法。前缘设计过程基于三次Bezier曲线,只需引入三个设计变量。使用该方法对可控扩散叶型前缘进行了重新设计,并采用计算流体力学方法比较了不同前缘形状对于叶型气动性能的影响。计算结果表明新型前缘在来流马赫数0.2和0.6两种下均能够有效抑制前缘分离泡的产生和发展,与圆弧形和椭圆形前缘相比叶型攻角范围分别扩大约1.2°和2.5°。对跨声转子叶片的前缘进行重新设计后,提高了动叶效率,扩大了稳定工作范围。
In order to optimize the shape of the leading edge of the compressor blade and improve the performance of the blade, a method of designing the leading edge of the continuous curved blade is proposed. The leading edge design process is based on cubic Bezier curves and requires only the introduction of three design variables. Using this method, the leading edge of controllable diffuser is redesigned and the influence of different leading edge shapes on the aerodynamic performance of the blade is compared by computational fluid dynamics. The calculated results show that the new leading edge can effectively suppress the generation and development of the leading edge bubble at Mach 0.2 and 0.6, respectively. Compared with the arc and the elliptical leading edge, ° and 2.5 °. After redesigning the leading edge of the transonic rotor blade, the rotor efficiency is improved and the stable working range is enlarged.