R0110重型燃气轮机燃烧室三维数值模拟  

3D Numerical Simulation of R0110 Heavy Duty Gas Turbine Combustor

作　　者：齐兵[1] 金戈[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》2009年第4期29-32,44,共5页Aeroengine

摘　　要：采用SIMPLE算法,应用带有旋流修正的k-ε双方程湍流模型及有限速率/涡耗散化学反应模型,对R0110重型燃气轮机逆流环管型燃烧室单个火焰筒进行了三维数值模拟计算。将计算出的燃烧室出口温度场的分布、品质及火焰筒壁温与试验结果进行了对比分析。燃烧室进口流量、温度、压力等气动参数均与试验时保持一致,火焰筒各部分空气流量也均按火焰筒空气流量分配试验结果给定。计算和对比分析的结果表明,计算得到的燃烧室出口温度场的分布、品质及火焰筒壁温分布与试验结果比较接近。3D numerical simulation of the single liner was performed for the ROllO heavy duty gas turbine reverse-flow cannular combustor using SIMPLE algorithm based on k-ε two-equation turbulent model with turbulent corrected and finite-rate/eddy dissipation chemistry reaction model. The comparative analyses between the calculation and experiment results with the distribution and quality of the combustor exist temperature field and the liner wall temperature were conducted. The aerodynamic parameters of the combustor inlet flow, temperature and pressure etc. were consistent with the test values. The airflow distributions of the liner were determined according to the experimental results. The results of the calculation and comparative analysis show that calculation results of the distribution and quality of the combustor exist temperature field and the distribution of liner wall temperature approach to the experimental results.

关 键 词：燃烧室 数值模拟 重型燃气轮机 温度场 品质 壁温 

分 类 号：TK124[动力工程及工程热物理—工程热物理] TU457[动力工程及工程热物理—热能工程]