摘要
为了满足高性能飞机对于高机动性、超声速巡航的需求,针对高推重比、高热力性能发动机的特点,设计了一种高温升燃烧室。利用分级燃烧、多点喷射、空气雾化喷嘴和发散小孔冷却等先进技术,解决了高温升燃烧室的技术难点。应用CFX软件对其进行了2个工况的数值模拟,得到了燃烧室的速度场、温度场的分布特性、污染物的生成情况。试验结果表明,燃烧室燃烧效率高,污染物排放低。
According to the characteristics of the high thrust-to-weight ratio and thermal performance of the aircraft engine, a high temperature rise combustor was designed to fulfill the requirements of advanced aircraft on good maneuverability and supercruise. The technical difficulties of high temperature rise combustor were solved by using staging, multi-point injection, air blast atomizer and effusion cooling technology. Numerical simulation which using CFX was conducted to study the performance of the combustor with two operating conditions, and the resultant characteristics of velocity and temperature field distribution, and emissions production were get, it showed the combustor can work satisfactorily, with high combustion efficiency and low emission.
出处
《航空科学技术》
2017年第2期13-19,共7页
Aeronautical Science & Technology
关键词
燃烧室
高温升
发散冷却
多点喷射
CFX
combustor
high temperature rise
effusion cooling
multipoint injection
CFX
