PROGRESS AND PROSPECT OF AERODYNAMIC EXPERIMENTAL RESEARCH ON LINEAR CASCADE
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摘要:平面叶栅气动试验传统上是验证压气机、涡轮的基元性能的主要手段, 近年来国内外研究人员利用平面叶栅开展了大量的流动测量试验, 以揭示叶栅内部复杂流动现象的本质和规律、探索减小叶栅内流动损失的方法. 本文从试验装置、测试技术和研究内容三个方面, 综述了近年来平面叶栅气动试验研究的进展情况. 首先介绍了平面叶栅试验装置的发展及提高平面叶栅试验段流场品质的措施; 其次介绍了叶栅气动试验采用的部分流场测试技术, 包括叶片表面压力场、叶片表面温度场、内流速度场及流场可视化等测试技术, 分析了这些测试技术的进展和存在的问题; 然后梳理了近年来平面叶栅试验研究的相关科学问题及进展, 包括跨音速叶栅中的激波研究, 叶顶间隙泄漏流动研究, 叶型优化研究, 多尺度非定常旋涡结构研究, 振动环境下叶栅流场研究等; 最后对平面叶栅气动试验研究方向进行了展望. 通过了解叶栅内复杂流动现象及本质, 为进一步探索和提高压气机、涡轮的气动性能提供技术支撑.Abstract:The aerodynamic experiment on linear cascade, which can provide numerous and systematic experimental results, is traditionally the main methods to verify the elementary aerodynamic performance of compressor and turbine. In recent years, the overseas and domestic researchers have carried out a large number of flow measurement experiments to reveal the internal flow mechanism and then explore methods to decrease flow loss of linear cascade flow field. In this paper, the overseas and domestic aerodynamic experiment research progress for linear cascade, especially for supersonic and transonic linear cascade has been reviewed and discussed from the viewpoints of experimental equipment, measurement technologies and experimental research content. Firstly, the development of linear cascade equipment and the methods for improving flow quality are reviewed, which can increase the inlet flow uniformity and outlet flow periodicity of the test section. Meanwhile, various aerodynamic experimental measurement technologies for linear cascade are discussed in detail, including measurements for blade surface pressure field, blade surface temperature field, flow velocity field and flow visualization. The existing problems and improvement methods for current measurement technologies are analyzed, respectively. Furthermore, mainly based on the decrease of flow loss, several key scientific problems and research progress for the aerodynamic experiment of linear cascade are discussed herein, including the interaction between shock wave and turbulence boundary layer in transonic cascade, tip leakage clearance flow research, baseline profile modification, multi-scale secondary flow vortex structures, unsteady flow characteristics, the cascade flow field research in vibration environment, and so on. Finally, based on the previous research, the prospects of the direction and the trends of linear cascade aerodynamic experimental research are discussed briefly, which may provide reference for future related studies. By understanding the phenomenon and mechanism of complex flow in cascade, it provides technical support for further improving the aerodynamic performance of compressor and turbine.
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图 3叶栅表面压力分布的PSP测量方案
Figure 3.Flow chart for surface pressure measurement of blade by PSP
图 6叶片表面温度分布的液晶测温方案
Figure 6.Flow chart for surface temperature distribution of cascade blade by liquid crystal
图 25平面叶栅气动试验研究思路和途径
Figure 25.Research approaches of aerodynamic experiment on linear cascade
图 26平面叶栅气动试验中的复杂流动
Figure 26.Complex flow phenomena of aerodynamic experiment on linear cascade
表 1试验段流场品质研究
Table 1.Investigation on flow field quality in test section
研究对象 研究内容 研究结果 栅前整流部件改进 阻尼网 阻尼网材料对流场品质的影响[2] 阻尼网整流性能受材料弹性模量影响较大 阻尼网与风洞壁面连接的刚性夹具装置优化[3] 带有可调张力机构的阻尼网装置可提高整流效果 阻尼网在风洞中的安装位置[4] 扩压段处安装阻尼网, 可减少流动分离 收缩段布置拌线和阻尼网联合整流[5] 试验段湍流强度和气流不均匀度减小 蜂窝器 蜂窝器和阻尼网组合整流效果[6] 相比阻尼网, 蜂窝器的整流效果并不明显 蜂窝器形状、尺寸对试验段整流效果的影响[7] 相同的长径比下, 蜂窝尺寸越小, 湍流强度越低 扩压段 扩压段采用柔性壁, 并将扩压段几何型线优化[8-9] 优化后可降低稳流段内阻尼网和蜂窝器引起的压力损失并提高整体的整流效果 叶栅侧壁边界层研究 叶片数目 叶片数目对高亚音叶栅风洞进口流场影响[10] 当叶片数小于7个时, 无法保证进口流场在至少2个通道内实现较好的均匀性 叶栅侧壁形状多参数优化[11-12] 可减少使用叶片的数目实现流场的周期性 单通道叶栅风洞 跨音单通道叶栅风洞设计[13] 可以耗费较低的风洞流量实现周期性的跨音速来流条件 通道二次流研究[14-15] 减小试验所需的流量, 且有利于光学测试的光路布置[14] 单通道进口两侧的排气装置可减弱“叶片”前缘的边界层厚度和马蹄涡强度[15] 气膜冷却效率研究[16] 能较好的实现跨音条件下不同形状气膜冷却孔对端壁冷却效率的影响研究 边界层抽吸 侧壁边界层抽吸与出口尾板相结合 对高亚音速气流, 需联合调节侧壁边界层抽吸量和尾板位置[17] 栅后流场周期性研究 尾板 采用可转动尾板且在尾板上开设一定角度的斜孔[18-19] 保证出口侧壁附近气流不受外界大气干扰和混合的影响, 同时避免了激波在尾板表面发生反射 尾板开孔率、开孔直径等参数对栅后气流周期性的影响[20-21] 拆除压力侧尾板, 同时调整边界层抽吸量和尾板转动角度[22] 双层侧壁且内壁可调, 作为叶栅的前挡板和尾板[23-24] 能实现叶栅中间两个通道的周期性 
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表 2国内外关于控制叶顶间隙泄漏流的叶栅试验研究
Table 2.Overseas and domestic control schemes of tip clearance leakage flow on linear cascade
控制手段 研究内容 研究结果 叶顶喷气 从叶顶表面的污垢清除孔喷出冷却气体[99-100] 间隙较小时, 喷出气体能碍间隙流动的发展; 间隙较大时效果不明显 叶片前缘与叶顶间开设贯通通道, 形成射流[101] 喷射方向朝向压力侧时, 抑制效果较明显 叶片压力面上和叶顶间开设通孔, 形成射流[102] 对叶顶间隙泄漏流具有一定抑制作用 非设计条件工况, 叶顶喷气的抑制效果[103-104] 叶顶后部的孔要比前部的孔具有更好的抑制性能 凹槽/凹坑类叶顶结构 凹槽内部的旋涡流动对泄漏流的抑制效果[74, [105] 小间隙时, 控制作用明显; 间隙较大时, 控制作用减弱 其他新型凹槽结构 不同高度的台阶凹槽[106] 相比于普通凹槽叶顶和平叶顶, 能对间隙泄漏流动具有较好的抑制效果 非均匀厚度的凹槽[107] 开口凹槽[28] 加装横向肋条的凹槽[108] 泪滴状凹坑、勾槽[109] 泪滴状凹坑阵列结构由于没有微小边缘和尖端设计, 可承受更大的热应力 蜂窝型叶顶结构[110-111] 蜂窝腔内会形成较小的涡流, 从而阻碍间隙泄漏流动 叶顶增加小翼 压力侧小翼和吸力侧的小翼对泄漏流的控制效果[112-113] 小翼可减少泄漏流的驱动压差, 减少泄漏损失, 在压力侧增加小翼, 更为有效 下载:
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表 3端部二次流的主动控制试验研究
Table 3.Active flow control of endwall secondary flow
控制手段 研究内容 研究结果 边界层抽吸技术 端壁一侧开槽抽吸[133] 抽吸附近流动稳定, 另一侧端壁附近仍有分离流动 角涡位置处抽吸[134] 对角涡的抑制作用明显 叶片不同展向位置开槽抽吸[135] 吸力面局部位置抽吸会导致其他部分流场的恶化, 只有采用全叶展方向上抽吸能有效的消除吸力面上的流动分离 射流技术 稳定射流 端壁和吸力面联合射流吹扫[136] 端壁处吹气能减少二次流, 在吸力面吹气则可减少叶片表面边界层分离 合成射流 合成射流激发器的安装位置[137] 吸力面的合成射流可控制吸力面的流动分离, 当射流位于分离点上游时, 流动控制效果最好 合成射流相比于脉冲射流和稳定射流的
控制效果评判[138]合成射流在低激励幅值时的效率略低, 不需要任何的质量流量输入, 所节约的能量大概为激励器自身消耗能量的两倍 下载:
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