弧线型缝隙射流控制高负荷叶栅分离实验
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- 英文论文题名：Experimental investigation on jet separation control using improved curve slot in critically loaded compressor cascade
- 论文作者：胡加国 ; 王如根 ; 李仁康 ; 黄丹青 ; Li Qiushi
- 英文论文作者：HU Jiaguo ; WANG Rugen ; Li Renkang ; Li Qiushi ; School of Aeronautics and Astronautics Engineering ; Air Force Engineering University
- 年：2016
- 作者机构：空军工程大学航空航天工程学院;School of Aeronautics and Astronautics Engineering, Air Force Engineering University;
- 论文关键词：压气机叶栅 ; 高负荷 ; 缝隙射流 ; 流动控制 ; 角区分离
- 英文论文关键词：Compressor cascade ; highly loaded ; slot jet ; flow control ; corner separation
- 会议召开时间：2016-11-25
- 会议录名称：2016年航空科学与技术全国博士生学术论坛摘要集
- 语种：中文
- 分类号：V231.3
- 学会代码：XBHH
- 会议名称：2016年航空科学与技术全国博士生学术论坛
- 会议地点：中国陕西西安
- 主办单位：西北工业大学研究生院、中国高校航空学院院长联席会
- 学会名称：西北工业大学航空学院
- 页数：2
- 文件大小：572k
- 原文格式：D
- 会议级别：全国
摘要
叶栅吸力面分离与角区堵塞是压气机流动损失的主要来源之一,也是失速的可能诱因。本文在前期设计的直线型缝隙射流控制叶栅分离思想的基础上,提出一种改进的圆弧型开缝射流方案,并使用高负荷叶栅做验证实验。实验表明,缝隙射流一方面减小了叶栅尾缘分离的宽度,提高了角区堵塞的气流速度,降低了分离流动损失;另一方面,抑制了叶栅通道内的复杂二次流与旋涡结构,出口流场更加均匀。在0°-6°攻角下,平均总压损失降低了16.6%-22.8%。但在-3°攻角下提高了2.8%,原因是射流缝出口在分离点之前。在-3°-6°攻角下,平均气流转折角提高了0.65°-2.99°。随着攻角增大原型叶栅的静压升系数迅速降低而丧失增压能力,开缝叶栅则保持在原型叶栅0°攻角的压升水平之上。综合叶栅气动性能参数,开缝叶栅的稳定工作的进气攻角范围至少扩宽了+3°。
The source of lose in compressor cascade mainly comes from the general suction side separation and corner stall, and also the possible inducement of flow instability. Based on the previously designed jet separation control approach using a linear slot, this paper develops an improved curve slot and then conducts experiments study to assess the flow control effects. The measurements show that the slot jet is able to reduce the width of cascade separation and accelerate the flow speed in corner stall, leading to a decrease of flow lose. The jet flow also suppresses the complex secondary flow and vertices in cascade passage, leading to a relatively clear outlet flow field. At incidence angles from 0° to-6°, the averaged total pressure lose reduces 16.6%-22.8%, but a little increase by 2.8% at-3° as the outlet of jet flow is upstream the separation point. At-3°-6°, the averaged flow turning angle increases 0.65°-2.99°. With the increase of incidence angle, the static pressure rise coefficient rapidly decrease and finally loses in baseline cascade, while the slot cascade remains its pressure rise higher than that of baseline cascade at 0°. Based on the cascade aerodynamic performances, the stable range of operating incidence angles enlarges at least +3° in slot cascade.
The source of lose in compressor cascade mainly comes from the general suction side separation and corner stall, and also the possible inducement of flow instability. Based on the previously designed jet separation control approach using a linear slot, this paper develops an improved curve slot and then conducts experiments study to assess the flow control effects. The measurements show that the slot jet is able to reduce the width of cascade separation and accelerate the flow speed in corner stall, leading to a decrease of flow lose. The jet flow also suppresses the complex secondary flow and vertices in cascade passage, leading to a relatively clear outlet flow field. At incidence angles from 0° to-6°, the averaged total pressure lose reduces 16.6%-22.8%, but a little increase by 2.8% at-3° as the outlet of jet flow is upstream the separation point. At-3°-6°, the averaged flow turning angle increases 0.65°-2.99°. With the increase of incidence angle, the static pressure rise coefficient rapidly decrease and finally loses in baseline cascade, while the slot cascade remains its pressure rise higher than that of baseline cascade at 0°. Based on the cascade aerodynamic performances, the stable range of operating incidence angles enlarges at least +3° in slot cascade.
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