Experimental investigation on flow control of corner separation in a compressor cascade
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摘要:
角区分离是航空压气机内部一种固有的流动分离现象，而控制角区分离是减小压气机流动损失、提高其气动性能的重要手段之一。为了加深对角区分离流动机理及相关控制技术的认识，本文基于自主设计的压气机叶栅设计了叶身/端壁融合（BBEW）、涡流发生器（VG）以及两者复合调控共3种被动控制方案，利用粒子图像测速技术（PIV），在低速叶栅风洞中完成了不同攻角与流速下速度场的详细测量。实验结果表明：所设计的BBEW控制叶栅对角区分离抑制有限，部分工况下还会加剧分离；而VG控制叶栅与复合调控叶栅可以通过尾迹涡干扰分离剪切层的稳定性，从而促进主流与低能流体的掺混，增强分离区的动能，有效抑制角区分离。
Abstract:Corner separation is an inherent flow instability phenomenon in a compressor cascade, and its control is an important component of strategies to reduce flow loss and improve the aerodynamic performance of compressors. To deepen understanding of flow mechanisms associated with corner separation and techniques for controlling it, three passive control schemes, i.e., blended blade and endwall (BBEW), vortex generator (VG) and their compound control scheme, were designed based on the customized compressor cascade. Particle image velocimetry (PIV) was used to measure the velocity distribution at different attack angles and velocities in a low-speed cascade wind tunnel. The experimental results showed that the designed BBEW control cascade had limited inhibition on corner separation, and it aggravated the separation under some operating conditions. The cascade with VG can disturb and break the separated shear layer by the wake vortices, helping to promote the mixing of the main flow and low energy fluids, enhance the kinetic energy of the separation zone, and effectively restrain the corner separation.
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图 11 时均湍动能云图（5°攻角）
Figure 11. Mean turbulent kinetic energy distribution （5° attack angle）
表 1 原型叶栅与VG主要几何参数
Table 1. Main geometrical parameters of prototype cascade and VG
参数 数值 叶片安装角γ/（°） 10 叶片弦长C/mm 50 叶片轴向弦长CX /mm 48 叶片栅距t/mm 27 转盘可调攻角i/（°） −20～15 VG与叶片前缘轴向距离ZVG /mm 3.2 VG与叶片前缘周向距离YVG /mm 9.9 VG与轴向夹角β/（°） 37 
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表 2 实验条件设置
Table 2. Experimental setup
i/（°） h/mm U∞/（m/s） Rec/104 0 6 6 2.1 5 6 6 2.1 0 6 9 3.1 5 6 9 3.1
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表 3 时均流向速度与流向脉动速度不确定度
Table 3. Uncertainty of time-averaged streamwise velocity and streamwise velocity fluctuation
% 不确定度 Rec=2.1×104 Rec=3.1×104 $\varepsilon （\overline u ） /{U_\infty }$ 0.70 0.67 $\varepsilon （{u_{{\text{rms}}}}） /{U_\infty }$ 0.50 0.48
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