摘要
以某小型回流燃烧室为基础验证平台,试验研究改变燃油喷嘴插入火焰筒涡流器组件深度对燃烧室出口温度场的影响,并对试验结果进行了比较和分析.结果表明:对同一燃烧室,燃油喷嘴与火焰筒涡流器组件之间有一个最佳的轴向位置,此时的燃烧室的出口温度分布系数最小;在相同的燃烧室工作状态,采用不同喷雾锥角的燃油喷嘴,这个最佳位置不同.该研究为燃烧室出口温度场的调试及燃烧室的研制提供了一条有效的技术途径.
Based on a testing platform of a small-sized reverse combustor,the effect of different axial locations of fuel nozzle in the swirler on combustor outlet temperature field is studied by experiment. And, the experimental results are also compared and analyzed. Experimental data show that,for the same combustor,there is an optimized axial location between the fuel nozzle and the swirler. In such case,the pattern factor of outlet temperature is minimum;Under the operating state of the same combustor,the optimized axial location of the fuel nozzle changes with the fuel nozzle spray angle. This study thus provides an effective technical approach to adjust the outlet temperature field and develop the combustor.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2007年第8期1222-1226,共5页
Journal of Aerospace Power
关键词
航空、航天推进系统
回流燃烧室
燃油喷嘴轴向位置
出口温度分布系数
试验研究
温度场调试
aerospace propulsion system
reverse combustor
axial location of fuel nozzle
pattern factor of outlet temperature
experimental investigation
temperature field adjustment
