摘要
针对发动机燃烧室由于高温升和低污染而使可用冷却空气大量减少的技术难题,设计了一套切向进气发散小孔的单管燃烧室模型.使用热流固耦合方法,通过对Navier-Stokes(N-S)方程的求解,对其流场特性和火焰筒壁温进行了数值模拟研究.计算在三维坐标系下,采用拉格朗日法计算燃油颗粒的轨迹,非预混模型计算燃烧,离散坐标模型计算辐射,使用标准k-ε湍流模型,在固壁附近运用壁面函数法,计算了两种工况的火焰筒壁温分布.结果表明,在燃烧室总油气比为0.046,冷却空气质量分数为30%,进口空气总温为830 K,总压为3 MPa工况下,燃烧室最高壁温为1 015 K,温度梯度最大为22.5 K/cm,完全满足推质比为12一级的军用发动机和民用发动机对燃烧室火焰筒在冷却空气质量分数为30%、总油气比为0.046条件下对于壁温的要求.
To solve technical difficulties resulting from high temperature rise and low emission of new generation engine combustor,a single tube combustor model with tangential effusion cooling technology was designed.Numerical simulation was conducted to study the flow field characteristics and wall temperature distribution of combustor liner by solving Navier-Stokes（N-S） equations with thermal fluid-solid coupling method.The liner wall temperature distribution was computed under two conditions by three-dimensional coordinate system,the fuel particle trajectory by Lagrange method,the combustion by non-premixed model,the radiation by discrete ordinates model,the turbulence by the standard k-ε model,and the neighborhood of the solid wall by the wall-function.The results show that,at the 0.046 fuel-air ratio condition,30% cooling air mass fraction,830 K inlet air total temperature and 3 MPa inlet air total pressure,the maximum wall temperature is 1 015 K and the maximum temperature gradient is 22.5 K/cm,which meet the need of wall temperature level for 12 thrust-mass ratio military engines and low emission civil engines at 30% cooling air mass fraction,and 0.046 fuel-air ratio condition.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2011年第5期1052-1058,共7页
Journal of Aerospace Power
关键词
燃烧室
火焰筒
冷却
发散小孔
高温升
低污染燃烧
combustor
liner
cooling
effusion hole
high temperature rise
low emission combustion
