摘要
采用数值模拟方法对燃用天然气的某型航改燃气轮机环形燃烧室进行三维流场分析。根据改型后燃气轮机的结构特点建立了真实的三维计算几何模型;计算中采用SIMPLE算法,可利用k-ε双方程湍流模型、六通量辐射模型、非绝热概率密度函数(PDF)燃烧模型及热力型NO模型对燃烧流动进行数值模拟,分析了燃气轮机环形燃烧室在3种状态下燃烧流场的性能。计算结果表明:在3种状态下的燃烧流场和燃烧性能均能达到设计状态。
The three-dimensional flow field of annular combustor for aero-derivative gas turbine burning gas fuel. was numerically simulated. The real three-dimensional geometry model was built based on the structural characteristics of aero-derivative gas turbine. The numerical simulation of the combustor flow was performed based on SIMPLE algorithm, using k-ε two-equation turbulence model, six-flux heat radiation model, nonadiabatic probability density function（PDF） combustion model and thermal NO model. The performance of the combustion flow field at the three conditions was analyzed for the gas turbine annular combustor. The calculation results showed that the flow field characteristics and combustion performance of the combustor could reach the design targets in the three conditions.
出处
《航空发动机》
2009年第6期22-24,共3页
Aeroengine
关键词
航改燃气轮机
环形燃烧室
燃烧流场
燃烧性能
数值模拟
aero-derivative gas turbine
annular combustor
combustion flow field
combustion performance
numerical simulation
