| 带不同凹腔结构涡轮问燃烧室数值模拟 |
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| 引用本文： | 莫妲,唐豪,李明,郑海飞.带不同凹腔结构涡轮问燃烧室数值模拟[J].航空发动机,2012,38(1):33-36. |
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| 作者姓名： | 莫妲 唐豪 李明 郑海飞 |
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| 作者单位： | 南京航空航天大学能源与动力学院 |
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| 基金项目： | 国家自然科学基金(51076064);江苏省“六大人才高峰”项目资助 |
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| 摘 要： | 为了提高航空燃气涡轮发动机的推进效率和满足低排放的要求,提出了1种基于涡轮内补燃增推循环的超紧凑燃烧室──涡轮间燃烧室。建立了3种带不同轴向凹腔(AC)结构的TIB模型,比较了3种模型的流动性能和燃烧性能。计算结果表明:TIB的燃烧效率高达99.3%,AC结构的改变对燃烧效率影响较小,但对温度场分布影响较大。
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| 关 键 词： | 涡轮间燃烧室 超紧凑燃烧室 数值模拟 凹腔结构 温度分布 燃烧性能 |
Numerical Simulation of Turbine Inter-Blade Burner(TIB) with Different Axial Cavity Shapes |
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| Authors: | MO Da TANG Hao LI Ming ZHENG Hai-fei |
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| Institution: | (College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China) |
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| Abstract: | In order to improve thrust efficiency of aeroengine and meet the requirement of low emissions,a Turbine Inter-blade Burner(TIB) based on the new Ultra-Compact Combustor(UCC) technology was proposed.Three cases of TIB with different Axial Cavity(AC) were designed and their flowfields and combustion performance were contrasted.The results show the combustion efficiency of TIB is almost 99.3%,which suggests AC has little impact of combustion efficiency,but it affects the temperature distribution. |
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| Keywords: | Turbine Inter-blade Burner Ultra-Compact Combustor numerical simulation axial cavity temperature distribution combustion performance |
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