摘要
应用CFD方法对航改QD128燃气轮机燃烧室性能进行了数值模拟。模拟结果表明:燃烧室流量分配设计基本合理,燃烧室内流场分布符合设计规律;燃烧室出口平均温度为1 298K,热点温度1 486K,径向温度分布曲线符合设计要求,OTDF=0.280,RTDF=0.086,略高于航机水平。模拟结果丰富了QD128燃机性能指标,为该机的运行、改进提供了可靠的参考依据。
Numerical simulation of combustor performance of QD128 gas turbine was finished using CFD method. The results indicated ： Flow distribution of combustor is reasonable, velocity field of combustor meets the design requirements. Outlet average temperature is 1 298K, hot spot temperature is 1 486K, the temperature distribution curve meets the design requirements, and OTDF = 0. 280, RTDF = 0. 086, which are slightly higher than the level of prototype aircrafts. The results enrich the design data of QD128 gas turbine,and provide reliable reference for the running and improving.
出处
《汽轮机技术》
北大核心
2012年第2期117-119,共3页
Turbine Technology
基金
国家863项目(2002AA503010)
关键词
燃气轮机
燃烧室
流场
温度场
数值模拟
gas turbine
combustor
velocity field
temperature field
numerical simulation
