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孔隙射流结构对扩压叶栅出口流场特性的影响
  • 期刊名称:航空动力学报
  • 时间:0
  • 页码:1364-1371
  • 语言:中文
  • 分类:V231.3[航空宇航科学与技术—航空宇航推进理论与工程;航空宇航科学技术]
  • 作者机构:[1]哈尔滨工业大学能源科学与工程学院,哈尔滨150001
  • 相关基金:国家自然科学基金(50876023);国家重点基础研究发展规划“973”项目(2007CB210100)高等学校博士学科点专项科研基金(20060213007)
  • 相关项目:柯恩达效应在燃机涡轮中作用机理的研究
作者: 宋彦萍|
中文摘要:

实验研究带有孔隙射流结构的某大折转角直扩压叶栅在设计冲角下的出口流场特性,分析了不同孔隙射流位置对出口流场的影响.结果表明:在叶片表面开孔隙后,降低开孔隙的叶高处出口气流折转能力,使叶栅性能下降;孔隙射流使尾迹速度增加,相应的尾迹损失降低,尾迹区范围减小,同时出口气流角沿节距方向分布更加均匀,开孔位置越靠近叶展中部,孔隙射流对尾迹的影响越明显;开多孔方案对叶栅出口流场的影响要强于单孔方案.

英文摘要:

Experiments of a large turning angle linear compressor cascade with air injection slot were carried out, and detailed outlet flow field characteristics at design incidence were described in this paper. The results show that air injection through slots decreases the turning and diffusion of compressor cascade, the aerodynamic performance of the cascade also decreases; air injection energizes the low energy fluid near wake, increases the velocity of the wake, thus the size of the wake region reduces significantly, pitch-wise distribution of flow outlet angle becomes more uniform, slot position has great effect on wake especially with slot located near mid-span; multi-slot configurations have greater effect on outlet flow field than one-slot configurations.

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