北京航空航天大学学报 ›› 2011, Vol. 37 ›› Issue (1): 15-20.

• 论文 • 上一篇    下一篇

引气对跨声轴流压气机性能的影响

赵斌, 李绍斌, 周盛   

  1. 北京航空航天大学 航空发动机气动热力重点实验室, 北京 100191
  • 收稿日期:2010-06-01 出版日期:2011-01-31 发布日期:2011-01-28
  • 作者简介:赵 斌(1983-),男,河南兰考人,博士生,zhaobinaero@gmail.com.
  • 基金资助:

    国家自然科学基金资助项目(60934001); "凡舟"青年科研基金资助项目(20090403)

Bleeding impact on performance of transonic axial compressor

Zhao Bin, Li Shaobin, Zhou Sheng   

  1. National Key Laboratory on Aero-Engines, Beijing University of Aeronautics and Astronautics, Beijing 100191, China
  • Received:2010-06-01 Online:2011-01-31 Published:2011-01-28

摘要: 以单级跨声轴流压气机NASA Stage35为研究对象,根据影响转子和静子通道流动的主要物理现象分别设计了多种引气方案.通过数值模拟比较分析引气与不引气状态下压气机的详细流场,结合实验测量结果,研究转子机匣端壁引气位置以及静子机匣端壁引气量对压气机性能及流场的影响.结果表明:转子机匣端壁引气能够有效控制间隙泄漏流的发展,减小叶尖损失,提升压气机性能.不同的引气槽结构和轴向位置对间隙流动的影响机理不相同;静子机匣端壁引气能够有效减小静子叶排损失,提升压气机效率.

Abstract: By analyzing the transonic single-stage compressors NASA Stage35, multiple bleeding plans were presented according to the physical phenomena of the flow in rotor and stator passage. Combined with experimental results, compressor flow field with and without air bleeding were compared to study the impact of the rotor casing bleeding position and the stator casing bleeding amount on the compressor flow field and performance. The results show that rotor casing bleeding can inhibit the development of tip leakage flow in the passage circumferential, reduce the flow loss of the tip region and enhance the compressor performance. The impact mechanisms on the tip flow field vary as the bleeding positions and structures change. Stator casing bleeding can cut the flow loss and improve the compressor efficiency.

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