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[1]高翔宇,孙纪国,田 原.缩比推力室甲烷传热试验研究[J].火箭推进,2013,39(04):19-23.
　GAO Xiang-yu,SUN Ji-guo,TIAN Yuan.Experimental study on methane heat transfer test system[J].Journal of Rocket Propulsion,2013,39(04):19-23.
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缩比推力室甲烷传热试验研究

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 39 期数: 2013年04期 页码: 19-23 栏目: 研究与设计 出版日期: 2013-08-30
Title:
Experimental study on methane heat transfer test system
文章编号:
1672-9374(2013)04-0019-05
作者:
高翔宇; 孙纪国; 田 原
北京航天动力研究所，北京 100076
Author(s):
GAO Xiang-yu;  SUN Ji-guo;  TIAN Yuan
Beijing Aerospace Propulsion Institute, Beijing 100076, China
关键词:
甲烷; 对流换热; 推力室; 液体火箭发动机
分类号:
V434-34
文献标志码:
A
摘要:
为了研究火箭发动机推力室冷却通道内的甲烷传热和流阻特性，研制了缩比推力室甲烷传热试验系统，并以推力室挤压热试验的形式进行了5次超临界甲烷传热试验和2次亚临界甲烷传热试验研究。超临界甲烷传热试验燃烧室压力为5.5~7.5 MPa，燃烧室氢氧混合比约为6.8，甲烷温度为128~230 K，甲烷冷却剂流量为5~7 kg/s，甲烷冷却剂入口压力为8.3~11.7 MPa。亚临界甲烷传热试验的室压约为4 MPa，氢氧混合比2.8，甲烷温度为：128~189 K，甲烷冷却剂流量约为2.9 kg/s，甲烷入口压力为3~
Abstract:
A methane heat transfer test system was built to investigate the methane heat transfer and flow resistance characters in the coolant channel of thrust chamber in liquid rocket engine. Five supercritical hot fire tests and two subcritical hot fire tests for methane heat transfer study were performed in trust chamber extrusion heat test. The conditions of supercritical methane heat transfer tests are combustion chamber pressure of 5.5~7.5 MPa, O/H mixture ratio of about 6.8, methane temperature of 128~230 K, methane coolant mass flow of 5~7 kg/s, methane coolant inlet pressure of 8.3~11.7 MPa. The conditions of subcritical methane heat transfer tests are combustion chamber pressure of about 4 MPa, O/H mixture ratio of about 2.8, methane temperature of 128~189 K, methane coolant mass flow of about 2.9 kg/s, coolant inlet pressure of 3~3.5 MPa. The heat transfer and flow resistance characters of liq

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备注/Memo

收稿日期：2012-08-24；修回日期：2013-06-05
基金项目：国家863项目（2006AA722067）
作者简介：高翔宇（1980—），男，工程师，研究领域为液体火箭发动机燃烧装置设计

更新日期/Last Update: 1900-01-01