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王克菲,骆剑霞,田淑青,朱惠人,刘聪.叶片吸力面不同位置处气膜冷却特性对比[J].航空动力学报,2017,32(6):1281~1288
叶片吸力面不同位置处气膜冷却特性对比
Film cooling performance comparison at different positions on blade suction side
投稿时间:2016-05-05  
DOI:10.13224/j.cnki.jasp.2017.06.001
中文关键词:  雷诺数  马赫数  吸力面  气膜孔  曲率
英文关键词:Reynolds number  Mach number  suction side  film cooling hole  curvature
基金项目:上海市科学技术委员会资助项目(14DZ1104600)
作者单位
王克菲 中国航空发动机集团有限公司 商用航空发动机有限责任公司 设计研发中心上海 201108 
骆剑霞 中国航空发动机集团有限公司 商用航空发动机有限责任公司 设计研发中心上海 201108 
田淑青 中国航空发动机集团有限公司 商用航空发动机有限责任公司 设计研发中心上海 201108 
朱惠人 西北工业大学 动力与能源学院西安 710072 
刘聪 西北工业大学 动力与能源学院西安 710072 
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中文摘要:
      在跨声速叶栅通道内,试验研究了叶片吸力面不同位置处的气膜冷却特性,详细地分析吸力面两个位置处的簸箕孔型在主流进口雷诺数为3.7×105、出口马赫数为0.81,0.91,1.01及气膜吹风比为0.6~2.1条件下的气膜冷却效率.结果表明:气膜孔2位于大的叶片曲率位置处,该位置处主流能使得射流更好地贴附在壁面上,但是该影响有利有弊.在小吹风比下,气膜孔射流本身就能很好地贴附壁面,因而主流使得气膜贴壁较好的作用不强,而主流使得气膜展向扩展不易的负面影响却比较明显.在大吹风比下,气膜射流法向分量较大,气膜容易脱离壁面,此时,气膜孔2由于主流作用使得气膜更好地贴附在壁面上,气膜冷却效率有较大提升.
英文摘要:
      Film cooling performances of two fan shaped film holes at different positions on blade suction side were experimentally studied in a linear transonic cascade. The film cooling effectiveness of the fan shaped film holes on blade suction side was measured at mainstream inlet Reynolds number of 3.7×105, different mainstream exit Mach number of 0.81, 0.91,1.01, and different blowing ratio of 0.6-2.1. Results shows the film hole 2 is at the position with higher curvature, where the mainstream forces the coolant to better flow along the surface, however, this has both advantages and disadvantages. At smaller blowing ratio, the jet of film hole can flow close to the wall itself, so the advantage of the mainstream isnt obvious, but the mainstream forces the coolant to flow downstream and the coolant will be difficult for spanwise flow, bringing about lower film cooling effectiveness. At higher blowing ratio, the jet of film hole has large vertical velocity component, the coolant can be easily lifted off, then coolant of the film hole 2 can be forced to get close to the wall, so the film cooling effectiveness is increased substantially.
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