摘要
在保持燃烧室的扩压器尺寸、外机匣最大直径以及燃烧室出口尺寸与单环腔燃烧室一致的前提下,将燃烧室重新设计为径向分级的双环腔结构.采用相同的物理模型,用Fluent软件对单、双环腔主燃烧室分别进行全流程的三维数值模拟.结果表明,采用双环腔燃烧室,可明显提高燃烧室的总压恢复系数、燃烧效率;降低燃烧室出口温度分布系数、NOx/CO等污染的排放,尤其是慢车状态下的CO排放.用双环腔燃烧室置换单环腔燃烧室是可行的.
The combustor was redesigned into dual annular structure in radial direction, under the precondition that the diffuser, outer case and exit dimension are kept consistent with single annular combustor （SAC）. With the help of the same physical models,a 3-D simulation for full-flow process in both SAC and dual annular combustor （DAC） was conducted in the Fluent code. By using the DAC,it shows that the total-pressure recovery coefficient and combustion efficiency can be improved remarkably, the exit temperature distribution coefficient of the combustor and NOx/CO emission, especially for CO emission under slow running state, is reduced accordingly.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2008年第1期145-149,共5页
Journal of Aerospace Power
基金
航空基金(05C51033)
关键词
航空
航天推进系统
双环腔燃烧室
单环腔燃烧室
燃烧室设计
燃烧数值模拟
aerospace propulsion system
dual annular combustor （DAC） single annular combustor （SAC）
combustor-design
combustion simulation
