摘要
保持单环腔主燃烧室的扩压器,外机匣最大直径尺寸以及喷口不变的前提下,将其火焰筒结构重新设计为并联式双环腔结构,设计了6种不同旋流器组合的双环腔结构燃烧室.采用相同的物理模型(包括湍流模型、辐射模型、喷雾模型及污染排放模型等),对单、双环腔主燃烧室分别进行全流程的三维计算.给出了燃烧室的总压恢复系数、燃烧效率、燃烧室出口温度分布系数、污染排放指标等燃烧室性能参数.对比分析了单、双环腔燃烧室的计算结果.结果表明,双环腔燃烧室置换单环腔燃烧室是可行的,该研究可为大飞机低污染大法动机的设计提供技术支持.
In order to change a Single Annular Combustor（SAC） into a Dual Annular Combustor（DAC）, the authors kept the diffuser,outer case and atomize of the SAC unchanged,redesigned the combustor from a single annular structure into a dual annular structure,and designed six different structure DAC. Taking the same physical models（including the turbulence, radiation, spray and emission models）, simulations of three dimensional two-phase reacting turbulent flow in both the SAC and DAC were developed in the Fluent Code. The total-pressure recovery coefficient, temperature distribution and exhaust emission levels were given. Finally,by comparing the simulation results,the feasibility of displacing the SAC into DAC structure was certified.
出处
《吉首大学学报（自然科学版）》
CAS
2011年第2期65-70,共6页
Journal of Jishou University(Natural Sciences Edition)
基金
National Natural Science Foundation of China(90716025
50476005)
关键词
燃烧室设计
单环腔燃烧室
双环腔燃烧室
燃烧数值模拟
combustors design
single annular combustor
dual annular combustor
combustion simulation
