机械制造与自动化2024，Vol.53Issue(4)：54-57,86,5.DOI:10.19344/j.cnki.issn1671-5276.2024.04.009
蒸发式涡轮叶间燃烧室方案及性能研究
Study on Scheme and Performance of Evaporative Turbine Inter-blade Combustor
摘要
Abstract
In order to improve the overall performance and thermodynamic cycle mode of aero-engine,an evaporative turbine inter-blade combustion scheme was designed,and the combustion performance changes of the inter-blade combustor under different oil/gas ratios were studied experimentally.Parameters such as fuel distribution and component distribution in the combustor were obtained by numerical calculation.The results show that fuel atomization and stable combustion can be effectively promoted by using evaporative stabilizer in the inter-blade channel of the turbine guide.The maximum temperature rise of the inter-blade combustor is 694.4 K under test conditions,and the combustion efficiency is 90.3%.关键词
叶间燃烧/试验/燃烧性能/数值计算Key words
inter-blade combustion/experiment/combustion performance/numerical calculation分类
航空航天引用本文复制引用
张朋朋,何小民,丁国玉,陈丕敏,于镇潭..蒸发式涡轮叶间燃烧室方案及性能研究[J].机械制造与自动化,2024,53(4):54-57,86,5.基金项目
JKW基础加强重点研究项目(2021-JCJQ-ZD-062-11) （2021-JCJQ-ZD-062-11）
