某小型航空发动机燃烧室结构改进与分析  

Structure Improvement and Analysis of a Small Aero-engine Combustor

作　　者：何鹏[1] 谢建光[1] 胡仁高[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》2009年第4期21-24,47,共5页Gas Turbine Experiment and Research

摘　　要：本文就某小型航空发动机燃烧室在试验后发现的火焰筒外环出口端变形现象进行了研究,通过火焰筒强度计算和分析确定该现象是由于火焰筒头部结构刚性不足造成的。从改变火焰筒头部结构刚性入手,对比分析多种改进方案,借鉴现有国外先进发动机燃烧室火焰筒头部结构形式,并通过火焰筒强度计算分析、燃烧室性能数值模拟计算分析,改进了火焰筒头部结构形式,成功地排除了这一故障隐患,为后续发动机研制提供了参考和工程实践经验。Investigation was conducted to the distortion of combustor out ring of an aero-engine. The analysis showed that this phenomenon were due to the structure rigidity deficiency of flame tube head shield. Started from changing the structure rigidity of flame tube head shield, comparison and analysis of many kinds of improvement programs were made. With reference to overseas advanced engine chamber head shield, flame tube intensity calculation and combustor numerical simulation, improvements were achieved on the structure of flame tube head shield. It successfully eliminated the hidden trouble of failure and provided a precious design experience for the following engine development.

关 键 词：火焰筒 变形 结构刚性 数值模拟 

分 类 号：V235.113[航空宇航科学与技术—航空宇航推进理论与工程]