锥形排孔气膜冷却实验研究

推进技术 ›› 1998, Vol. 19 ›› Issue (3): 65-69.

锥形排孔气膜冷却实验研究

朱惠人,许都纯,刘松龄,王宝珑

西北工业大学航天工程学院;西北工业大学航天工程学院;西北工业大学航天工程学院;西北工业大学航天工程学院

发布日期:2021-08-15

FILM COOLING EXPERIMENTAL INVESTIGATION OF A ROW OF CONE SHAPED HOLES

Coll of Astronautics,Northwestern Polytechnical Univ,Xi′an,710072;Coll of Astronautics,Northwestern Polytechnical Univ,Xi′an,710072;Coll of Astronautics,Northwestern Polytechnical Univ,Xi′an,710072;Coll of Astronautics,Northwestern Polytechnical Univ,Xi′an,710072

Published:2021-08-15

摘要/Abstract

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。

关键词: 锥形孔;薄膜冷却;传热

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

Key words: Cone shaped hole+;Film cooling;Heat transfer

朱惠人,许都纯,刘松龄,王宝珑. 锥形排孔气膜冷却实验研究[J]. 推进技术, 1998, 19(3): 65-69.