前缘小叶片对高负荷扩压叶栅性能的影响

吴艳辉; 刘军; 安光耀; 陈智洋; 彭文辉

doi:10.13433/j.cnki.1003-8728.2017.0923

前缘小叶片对高负荷扩压叶栅性能的影响

doi: 10.13433/j.cnki.1003-8728.2017.0923

1.
西北工业大学动力与能源学院, 西安 710072;
2.
先进航空发动机协同创新中心, 北京 100191

基金项目:

国家自然科学基金项目（51276148，11572257，51536006）资助

详细信息

作者简介:
吴艳辉(1972-),教授,博士生导师,研究方向为叶轮机械气动热力学,wyh@nwpu.edu.cn

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- 被引次数: 0
出版历程
- 收稿日期: 2016-06-22
- 刊出日期: 2017-09-05

Effect of Leading Edge Little Blade on Performance of Highly Loaded Compressor Cascades

1.
School of Power and Energy, Northwestern Polytechnical University, Xi'an 710072, China;
2.
Collaborative Innovation Center for Advanced Aero-Engine, Beijing 100191, China

摘要

摘要: 针对压气机叶栅角区流动易分离的特点，提出一种在叶栅前缘安装小叶片来抑制角区分离的新型流动控制方法。在利用叶栅试验数据确认数值模拟的可靠性后，对不同攻角下安装小叶片前后叶栅的流场特性进行了数值研究。结果表明：在-6°到9°攻角范围内小叶片改善了扩压叶栅的气动性能，使得总压损失减小，静压升增大。小叶片能使叶栅角区前缘分离点后移，角区分离线后的反流区面积减小，改善了角区流动；更多的流体汇聚到中间叶高，增强叶中部载荷，提高了叶栅的扩压能力。
- 扩压叶栅 /
- 小叶片 /
- 流动控制 /
- 角区分离
Abstract: Because of the flow separation of the corner region of compressor cascade, a little blade installed in leading edge of cascades was proposed to control the separation of corner region. After confirming the reliability of numerical simulation method with experimental data, numerical simulations were carried out to explore the effects of little blade on the performance of cascade. The results show that the aerodynamic performance at the attack angle range of -6° and 9° is improved by the use of little blade. It also decreases the total pressure loss, arises the static pressure ratio. Furthermore, little blade makes leading edge separation point of cascades corner move back, the area of the reverse flow is decreased and corner flow is improved. More fluid converges to middle of cascade, which improves the diffusion capacity of the cascade.
- compressor cascades /
- little blade /
- flow control /
- flow separation

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参考文献(15)

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