开槽处理技术对叶片尾缘气流流动特性的影响

周敏; 王如根; 曹朝辉; 张相毅

开槽处理技术对叶片尾缘气流流动特性的影响

空军工程大学工程学院, 西安 710038

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出版历程
- 收稿日期: 2006-06-28
- 修回日期: 2006-12-13
- 刊出日期: 2007-07-28

Influence of slot treatment on flow performance of blade trailing edge

Engineering College, Air Force Engineering University, Xi'an, 710038, China

摘要

摘要: 提出了从叶片压力面向吸力面开槽的处理技术, 设计了在80%～94%h叶高位置的叶片尾缘处的开槽方案, 对叶片开槽处理后的压气机工作流场进行了数值分析.结果表明:小槽进口对叶片压力面附面层低速气流具有一定的抽吸作用, 使部分压力面附面层气流和部分主流被吸入小槽并进行加速, 这股气流将从小槽出口流出, 它能够对叶背尾缘附面层内低速气流进行加速, 从而控制或延缓附面层气流分离, 并进一步减弱了尾缘附面层分离气流与叶片尾流的掺混.深入分析流场发现, 小槽出口气流还可以控制吸力面附面层气流沿叶根向叶尖的潜移, 从而防止大量附面层气流在叶尖堆积.因此采用开槽处理技术能够有效改善叶片尾缘流场的流动特性, 提高流场的稳定性.
- 航空、航天推进系统 /
- 叶片尾缘 /
- 开槽处理 /
- 数值模拟 /
- 附面层气流
Abstract: The slot treatment technology from pressure surface to suction surface of blade was proposed,while a slot solution starting from 80%～94% blade height of blade trailing edge was designed to conduct numerical simulation of the flow field of compressor after slot treatment.The result shows that,the slot inlet could suck low-speed boundary layer flow on the pressure surface of the blade,such that some boundary layer flow and main flow will be sucked into the slot and speedily discharged from the slot outlet.The low-speed boundary layer flow on the blade trailing edge could be accelerated,enabling to control or restrain separation region of the boundary layer flow,and also reduce the mixing of separated boundary layer flow of trailing edge and the blade trailing flow.The in-depth analysis shows that,the slot outlet flow could also control the migration of boundary layer flow towards the blade tip along the blade root,thus avoiding accumulation of boundary layer flow on the tip.So,the slot treatment technology can help improve the flow performance and stability of the flow field of blade trailing edge.
- aerospace propulsion system /
- blade trailing edge /
- slot treatment /
- numerical simulation /
- boundary layer flow

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参考文献(8)

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