Research on the effect of leading edge shape on the performance of variable inlet guide vanes
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摘要:
为优化前缘提升可变弯度导叶气动性能，将圆形前缘改为椭圆型前缘和曲率连续前缘，通过数值模拟分析比对了不同前缘可变弯度导叶在不同工况下的性能，结果表明改型前缘产生的前缘吸力峰强度更低，使得叶片表面附面层流动状态更好，从而降低总压损失。前缘形状的影响随着后叶转角角度的变化而变化，小转角状态下，改型前缘可有效增大低损失攻角范围；大转角状态下，改型前缘在正攻角状态下优化效果明显，在来流攻角为4°时，改型前缘导叶的总压损失最多降低32.6%，负攻角状态则影响较小，在来流攻角为−4°时最多降低9.9%。说明前缘改型可有效提升可变弯度导叶的性能。
Abstract:To optimize the aerodynamic performance of variable-camber guide vanes with leading-edge modifications, the circular leading edges were redesigned into elliptical and continuously curved leading edges. Numerical simulations were conducted to analyze and compare the performance of these modified vanes under various operating conditions. The results showed that the modified leading edges generated lower suction peak intensity on the leading edge, leading to better boundary layer flow and consequently lower total pressure loss. The impact of leading-edge shape varied with changes in the rear leaf deflection angle. At small deflection angles, the modified leading edge can effectively increase the range of low-loss attack angles. At large deflection angles, the optimization effect of the modified leading edge was significant at positive attack angles. The total pressure loss of the modified leading-edge guide vane was reduced by up to 32.6% at an incoming attack angle of 4°, while the effect was less impactful at negative attack angles, with a maximum reduction of 9.9% at an incoming attack angle of −4°. The results indicate that the modification of the leading edge can effectively enhance the performance of variable-camber guide vanes.
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图 5 不同后叶转角情况下VIGV的总压损失对比
Figure 5. Comparison of total pressure loss of VIGV under different rear leaf angles
图 6 典型工况下VIGV性能对比
Figure 6. Comparison of VIGV performance under typical operating conditions
图 7 α=0°情况下不同前缘$ {C}_{p} $对比
Figure 7. Comparison of $ {C}_{p} $ for different leading edges under α=0°
图 8 Ma=0.60, α=0°工况下马赫数云图
Figure 8. Mach number contour map under condition Ma=0.60, α=0°
图 9 Ma=0.6，α=0°工况下来流攻角为6°时前叶附面层参数对比
Figure 9. Comparison of boundary layer parameters for the front vane when Ma=0.6, α=0° and the incoming flow attack angle is 6°
图 10 来流Ma=0.6，α=0°条件下来流攻角为0°时前叶附面层参数对比
Figure 10. Comparison of boundary layer parameters for the front vane when Ma=0.6, α=0° and the incoming flow attack angle is 0°
图 11 来流Ma=0.485, α=25°情况下，圆形前缘VIGV不同来流攻角工况下流动状态对比
Figure 11. Comparison of flow states under different angles of attack for a circular leading edge VIGV with incoming flow Ma=0.485, α=25°
图 12 后叶转角α 为25°，Ma为0.35不同来流攻角工况下熵增云图
Figure 12. Entropy increase contour map under different incoming flow attack angles when the back vane rotation angleα is 25° Ma is 0.3
图 13 来流Ma=0.35，α=25°条件下来流攻角为4°时后叶附面层参数对比
Figure 13. Comparison of boundary layer parameters for the back vane when Ma=0.35, α=25° and the incoming flow attack angle is 4°
图 14 来流Ma=0.35，α=25°条件下来流攻角为−4°时后叶附面层参数对比
Figure 14. Comparison of boundary layer parameters for the back vane when Ma=0.35, α=25° and the incoming flow attack angle is −4°
表 1 某压气机典型工况
Table 1. Typical working conditions of a compressor
压气机转速/% 后叶转角/（°） 进口马赫数 100 0 0.6 85 13 0.485 80 25 0.35 
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表 2 VIGV几何参数
Table 2. Geometric parameters of VIGV
参数 数值 弦长$ C $/mm 146.1 栅距$ b $/mm 100.62 稠度$ \tau $ 1.452 进口几何角$ {\beta }_{1} $/（°） 0 出口几何角$ {\beta }_{2} $/（°） −6.53 最大相对厚度$ {t}_{\max } $ 0.06 最大厚度相对位置e 0.41
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