Numerical simulation and experimental investigation on swirl distortion generator with variable curvature blade
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摘要:
为了研究进气旋流畸变对航空发动机整机及风扇/压气机部件气动性能与稳定性的影响，设计了一种由多个可变弯度叶片组成的旋流畸变发生器。通过结合计算流体动力学（CFD）数值仿真与试验方法，深入分析了旋流畸变发生器下游流场的特性，并对气动界面的旋流评价指标进行了评估。研究结果显示，通过调整旋流畸变发生器的叶片组合，能够在下游形成显著的整体涡和对涡。随着后段叶片安装角的增加以及来流马赫数的提升，旋流强度逐渐增强，在来流马赫数等于0.35时，整体涡发生器在气动界面上的最大值可达36.04°，而对涡发生器的最大值可达29.95°。
Abstract:To study the effect of inlet swirl distortion on the aerodynamic performance and stability of the entire engine and its fan/compressor components, a swirl distortion generator with variable curvature blades was designed. By combining computational fluid dynamics (CFD) numerical simulation with experimental methods, the characteristics of the flow field downstream of the swirl distortion generator were analyzed in depth, and the swirl evaluation indicators at the aerodynamic interface were assessed. The research results show that by adjusting the blade combination of the swirl distortion generator, significant bulk swirl and twin swirl can be formed downstream. As the blade stagger angle at the rear section increases and the incoming flow Mach number rises, the swirl intensity gradually increases. The maximum value of the bulk swirl generator at the aerodynamic interface can reach 36.04°, while the maximum value of the twin swirl generator can reach 29.95°.
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Key words:
- swirl distortion /
- variable curvature blade /
- bulk swirl /
- twin swirl /
- swirl intensity
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图 3 旋流畸变发生器三维模型图
Figure 3. Three-dimensional model diagram of swirl distortion generator
图 8 整体涡旋流角和速度矢量分布
Figure 8. Swirl angle and velocity vectors distribution of bulk swirl
图 10 AIP界面测环上旋流角沿周向分布情况
Figure 10. Circumferential distribution of swirl angle on measuring rings at AIP section
图 11 整体涡AIP界面不同测环的旋流畸变指标
Figure 11. Swirl distortion descriptors on different measuring rings of bulk swirl at AIP section
图 13 对涡发生器相对马赫数分布
Figure 13. Relative Mach number distribution of twin swirl generator
图 14 不同后段叶片安装角的对涡旋流角分布
Figure 14. Swirl angle distribution of twin swirl with different stagger angles
图 15 对涡发生器下游不同轴向界面极限流线
Figure 15. Limit streamlines of the twin swirl generator at different downstream axial sections
图 16 AIP界面测环上旋流角沿周向的分布情况
Figure 16. Circumferential distributions of swirl angle on three different rings at AIP section
图 17 对涡发生器AIP界面不同测环上旋流指标
Figure 17. Swirl distortion descriptors on different measuring rings of twin swirl generator at AIP section
图 19 扩张段叶片流动分离随来流马赫数变化情况
Figure 19. The flow separation of the blade in the expansion section changing with the Mach number
图 20 旋流强度随后段叶片安装角变化
Figure 20. Variation of swirl intensity with stagger angle of the rear blades
图 21 不同后段叶片安装角的整体涡0.87R旋流角分布
Figure 21. Distribution of swirl angle of bulk swirl at 0.87R with different stagger angles of the rear blades
图 22 不同后段叶片安装角的对涡0.87R旋流角分布
Figure 22. Distribution of swirl angle of twin swirl at 0.87R with different stagger angles of the rear blades
图 23 数值仿真和试验数据对比
Figure 23. Comparison of numerical simulation and experimental results
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