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锥形排孔气膜冷却实验研究

FILM COOLING EXPERIMENTAL INVESTIGATION OF A ROW OF CONESHAPED HOLES

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【作者】 朱惠人许都纯刘松龄王宝珑

【Author】 Zhu Huiren Xu Duchun Liu Songling Wang Baolong(Coll of Astronautics,Northwestern Polytechnical Univ,Xi′an,710072)

【机构】 西北工业大学航天工程学院

【摘要】 对五孔单排锥形孔气膜冷却进行了实验研究,测出了孔排下游的局部换热系数及冷却效率,并研究了喷气雷诺数及吹风比的影响。实验参数范围是:喷气雷诺数Re=10000~25000,吹风比M=0.3~2.0,测量分26个工况进行。

【Abstract】 Film cooling of a row of five coneshaped holes has been studied experimentallyLocal heat transfer coefficients and film cooling effectiveness of downstream of hole row were measured and the influences of coolant Reynolds number and blowing rate are describedThe ranges of these parameters are:the coolant Reynolds number from 10000 to 25000 and blowing rate from 03 to 20 Measures were performed for 26 conditions

【关键词】 锥形孔薄膜冷却传热
【Key words】 Coneshaped hole+Film coolingHeat transfer
  • 【文献出处】 推进技术 ,JOURNAL OF PROPULSION TECHNOLOGY , 编辑部邮箱 ,1998年03期
  • 【分类号】V233.5
  • 【被引频次】21
  • 【下载频次】112
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