QD128航改燃气轮机燃烧室数值模拟  

Numerical Simulation of QD128 Aero-Derivative Gas Turbine Combustor

作　　者：金戈[1] 张志学[1] 顾铭企[1] 

机构地区：[1]沈阳发动机设计研究所,沈阳110015

出　　处：《航空发动机》2008年第2期30-35,共6页Aeroengine

摘　　要：应用计算流体动力学软件FLUENT,对QD128航改燃气轮机燃烧室进行了三维数值模拟计算分析。为了验证数值计算结果的合理性,首先,对以航空煤油为燃料的航机燃烧室进行了CFD数值模拟计算,并将采用3种湍流模型得到的CFD计算结果与航机燃烧室性能试验结果进行了对比,确定了适合燃烧室数值模拟计算的湍流模型Realizable k-ε;然后,采用Realizable k-ε湍流模型,对燃用天然气的QD128燃气轮机燃烧室进行了数值模拟计算,根据其计算结果,对QD128燃气轮机燃烧室出口温度场进行了优化,并对改进后的燃烧室进行了CFD计算,计算结果表明改进措施是有效的。The 3D numerical simulation of the QD128 aero -derivative gas turbine combustor was performed by using computational fluid dynamics （ CFD ） software FLUENT. In order to demonstrate the reasonability of the numerical calculation results, firsdy, the CFD numerical simulation of the aeroengine combustor with kerosene was conducted by adopting three different turbulent models, and the appropriate turbulent model Realizable κ-ε was selected by comparing the CFD calculation results from three different turbulent models with test datum of aeroengine combustor performance. Then, the numerical simulation of QD128 gas turbine combustor with natural gas was performed by using the turbulent model, and the temperature field of combustor outlet was optimized according to the CFD results. The CFD results of modified combustor indicate that the improvement is effective.

关 键 词：航改燃气轮机 燃烧室 数值模拟 CFD 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程] TK124[动力工程及工程热物理—工程热物理]