压气机叶型出气边厚度修正及气动性能的比较验证

Increase Compressor Blade Trailing Edge Thickness and Aerodynamic Validation

采用Bezier曲线分段拟合NACA-65叶型的厚度分布,得到光滑的压气机叶型厚度分布曲线,并用于修改叶型出气边厚度,解决了局部点坐标修改造成的型线锯齿的问题。用数值模拟的方法对出气边厚度增加前后叶型的气动性能进行了比较,结果表明,适当地增加出气边厚度基本不会改变叶型表面的压力分布,对平均气流转折角的影响也很小。尾迹区有所增大,流道扩压能力有所降低。阻力系数增加,升力系数降低。

It is presented in this paper a new method of data fitting for NACA - 65 serious blade thickness distribution. Result can provide smooth thickness profile along blade camber line with locally increased trailing edge thickness. Zig - Zag line due to local point movement can be avoided. Aerodynamic performanee of the new blade shape was numerically analyzed to compare the influence of trailing edge thickness. Results showed that static pressure distribution and flow turning angle can be maintained with acceptable thickness modification. With enlarged wake flow region, lifting force is redueed while resistance force is increased.