推力室多孔面板发汗冷却试验研究  

Experimental study on porous plate transpiration cooling of thrust chamber

作　　者：高翔宇[1] 孙纪国 

机构地区：[1]北京航天动力研究所,北京100076

出　　处：《火箭推进》2011年第5期9-12,共4页Journal of Rocket Propulsion

基　　金：国家航天高技术项目

摘　　要：为了研究液体火箭发动机推力室喷注器多孔面板发汗冷却特性,以缩比推力室挤压热试验的形式开展了多孔面板发汗冷却特性研究,试验采用常温气氢对喷注器多孔面板进行发汗冷却。发汗冷却试验共进行5次,燃烧室压力为3.9～7.6 MPa,燃烧室氢氧混合比为2.8～7.2。研究结果表明在本试验研究状态下面板燃气侧温度为680～830 K,总结了推力室多孔面板渗透率与压降的工程关系式。Hot fire tests were performed on subscale thrust chamber to investigate the transpiration cooling characteristics of thrust chamber injector porous face plate cooled by H2 of room temperature. Five times tests were conducted under the conditions： combustion chamber pressure of 3.9-7.6 MPa,and O/F mixture ratio of 2.8-7.2.The investigation demonstrates that the hot gas wall temperature of the porous plate is 680-830 K under the test conditions.The engineering flow resistance function applied to thrust chamber porous face plate was obtained.

关 键 词：发汗冷却 多孔面板 液体火箭发动机 推力室 

分 类 号：V434-34[航空宇航科学与技术—航空宇航推进理论与工程]