摘要
介绍了液氧/煤油补燃火箭发动机整流栅的各种结构,简要叙述了空气吹风模拟试验研究方法与研究结果。利用Fluent软件对燃气弯管内流场进行了数值模拟,分析其流动与压力分布。建立了发动机整流栅声学特性的计算模型,采用变步长四阶龙格-库塔数值逼近方法计算声导纳,并对整流栅抑制高频燃烧不稳定性的机理进行了初步探讨。结果表明,整流栅除了影响燃气入口总压的均匀性之外,还可起到抑制高频燃烧不稳定性的作用。
Various configurations of the perforated gas distribution plate in the LOX/kerosene staged combustion engine were recounted and the air-blow simulation test of plate was introduced. Numerical simulation of the three-dimensional flow was completed with Fluent. The numerical cal- culation was carried out with 4-stage variation step Runge-Kutta algorithm using the derived 1-D model for acoustic characteristics analysis of the plate. In addition, the influence mechanism that the perforated plate of gas line on combustion instability was preliminarily discussed. The results indicate that the so damps the perforated distribution plate not only effects the distribution of the total pressrue but alcombustion instability of high frequency.
出处
《火箭推进》
CAS
2007年第2期1-6,共6页
Journal of Rocket Propulsion
关键词
液氧/煤油补燃发动机
整流栅
流场数值模拟
声学特性
冷吹风试验
高频
燃烧不稳定性
LOX/kerosene staged combustion rocket engine
perforated plate
numerical simu-lation
acoustic characteristics
airflow test
high-frequency combustion instability
