冲击加多斜孔双层壁冷却方式流量系数研究

推进技术 ›› 2000, Vol. 21 ›› Issue (5): 49-52.

冲击加多斜孔双层壁冷却方式流量系数研究

许全宏,林宇震,刘高恩

北京航空航天大学热动力研究所!北京100083;北京航空航天大学热动力研究所!北京100083;北京航空航天大学热动力研究所!北京100083

发布日期:2021-08-15
基金资助:
国家重点试验室基金资助项目

Discharge coefficient of double wall with discrete hole and inclined multihole for combustor liner

Inst of Thermal Power Engineering, Beijing Univ of Aeronautics & Astronautics, Beijing 100083,China;Inst of Thermal Power Engineering, Beijing Univ of Aeronautics & Astronautics, Beijing 100083,China;Inst of Thermal Power Engineering, Beijing Univ of Aeronautics & Astronautics, Beijing 100083,China

Published:2021-08-15

摘要/Abstract

摘要： 为了获得冲击加多斜孔双层壁冷却方式的流量系数 ,分别对两种孔排列方式的冲击和多斜孔实验板组合成的四组双层壁模型在相似理论指导下进行实验。研究压力参数从 0变化到 80时 ,流量系数的变化情况。另外讨论并分析了主流流量、孔排列方式、双层壁缝高的变化对流量系数的影响程度。为燃烧室设计和壁温预估提供依据。

关键词: 航空发动机;燃烧室;多斜孔壁;冷却;流量系数

Abstract: In order to determine the discharge coefficients for double wall cooling with discrete hole and inclined multi hole in combustor liner,an experimental investigation was performed for two different forms of hole arrangement Four test models were used in this study The variation of discharge coefficients with the change of pressure parameter from 0 to 80 was obtained In addition,the effects of main airflow,distance between the walls,the form of hole arrangement were analyzed and discussed This study can be useful in combustor design and its wall temperature prediction

Key words: Aircraft engine;Combustion chamber;Inclined multihole wass;Cooling;Flow coefficient

许全宏,林宇震,刘高恩. 冲击加多斜孔双层壁冷却方式流量系数研究[J]. 推进技术, 2000, 21(5): 49-52.