高温升火焰筒壁面及头部复合冷却设计分析  

Design Analysis for Compound Cooling of High Temperature Rise Combustor Wall & Head Shield

作　　者：李彬[1] 程波[1] 

机构地区：[1]中国燃气涡轮研究院,四川成都610500

出　　处：《燃气涡轮试验与研究》2007年第3期8-10,56,共4页Gas Turbine Experiment and Research

摘　　要：某燃烧室火焰筒壁面采用冲击+逆向对流+气膜冷却技术,火焰筒头部采用冲击+对流冷却技术。本文通过计算并与试验结果对比分析表明:该火焰筒的冷却设计基本合理、可行,经进一步的改进和完善后,可作为高温升燃烧室火焰筒的优选设计方案之一。One combustor flame tube wall was designed to use impingement-counterflow convection-film cooling technique, it＇s flame tube head shield to use impingement-convection cooling. In this paper, the calculated results were compared with experimental dada. Analyses indicated the compound cooling design of combustor flame tube is feasible. With further improvement, this design can be used as one of cooling schemes of high temperature rise combustor flame tube.

关 键 词：航空、航天推进系统 燃烧室 火焰筒 冷却 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]