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用于冲击/发散双层壁冷却数值模拟的源项法模型
引用本文:张玉芳,黄望全.用于冲击/发散双层壁冷却数值模拟的源项法模型[J].南京航空航天大学学报,2017,49(S1):24-29.
作者姓名:张玉芳  黄望全
作者单位:中国航发商用航空发动机有限责任公司,上海,200241
摘    要:为了避免冷却孔内的网格划分从而减小计算量,将源项法模型应用到冲击加发散双层壁冷却结构的数值模拟中,并分析了网格设置和负能量源离散方式的影响。结果表明:源项法模型能较准确地预测综合冷效的变化趋势;在本文计算范围内,当发散孔入口/出口处面上平均面网格数超过一定量时,数值模拟结果不再随入口/出口处面上网格密度而变化;发散孔热侧壁面附近第一层网格高度对计算结果影响较大,较合适的高度设置是小于或等于0.05倍发散孔直径;固体内负能量源对应源项应均匀地加载在多个体单元上。

关 键 词:航空发动机  双层壁冷却  源项法模型  数值模拟

Source Term Model for Impingement/Effusion Double-Wall Cooling Numerical Simulation
ZHANG Yufang,HUANG Wangquan.Source Term Model for Impingement/Effusion Double-Wall Cooling Numerical Simulation[J].Journal of Nanjing University of Aeronautics & Astronautics,2017,49(S1):24-29.
Authors:ZHANG Yufang  HUANG Wangquan
Institution:AECC Commercial Aircraft Engine CO, LTD., Shanghai, 200241, China
Abstract:In order to avoid the meshing of discrete holes and to reduce computational cost, source term model is used for impingement/effusion double-wall cooling numerical simulation, and the effects of grid setups and heat sink discretization are analyzed. It has been concluded that overall effectiveness results can predict by source term model match the trend of experimental data.When the average number of face mesh on inlet/outlet of effusion hole is larger than a certain value, numerical results do not change with face mesh density on inlet/outlet of effusion hole.The height of first prism layer near the hot side of effusion wall has an important effect on the numerical results, and the proper setupof height is less than or equals to 0.05 hole diameter. Heat sink should be discretized on several volume cells of solid zone.
Keywords:aircraft engine  double-wall cooling  source term model  numerical  simulation
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