摘要
为解决高温升燃烧室点火、慢车工况的燃烧稳定性与起飞、巡航工况下高效率低冒烟燃烧之间的矛盾,对采用中心分级技术的双级旋流多点喷射直接混合(TAMDIM)组织燃烧技术的单头部燃烧室进行了试验,试验状态为慢车、起飞、亚声速巡航。通过试验获取了各个工况下燃烧室的燃烧效率、火焰筒壁温分布及冒烟值。TAMDIM燃烧室除慢车工况的燃烧效率小于0.99外,其余工况的燃烧效率均大于0.995,采用燃油分级对燃烧室效率影响很小。多斜孔发散冷却有良好的冷却能力,使得火焰筒壁温在燃烧室温升1157K下仅1005K。燃烧室在高油气比状态下冒烟数小于10,满足ICAO规定的要求。
In order to solve the problem of ignition, stable combustion and combustion efficiency in the high temperature rise combustor,the idle,cruise and take-off conditions of experiment investigation were conducted on single-dome combustor using twin annular muti-point direct injection mixing（TAMDIM） combustion technology. The results of experiment include combustion efficiency,flame tube wall temperature and combustion smoke. The investigation results show that combustion efficiency of idle condition is near 0.99 and exceed0.995 under other conditions. Fule stage has less impact on combustion efficiency in the cruise and take-off condition. The effusion cooled flame tube has good cooling performance. The flame tube wall temperature is only1005 K when the temperature rise is 1157 K. The smoke number is below 10 at high fuel air ratio condition,which meets the requirements of ICAO.
出处
《推进技术》
EI
CAS
CSCD
北大核心
2016年第9期1720-1726,共7页
Journal of Propulsion Technology
关键词
双级旋流
多点喷射
高温升燃烧室
燃烧效率
火焰筒壁温
Twin annular swirler
Muti-point direct injection
High temperature rise combustor
Combustion efficiency
Flame tube wall temperature
