| 燃油分级比对LESS燃烧室压力振荡频率的影响 |
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| 引用本文： | 秦皓,汤冠琼,林宇震,李继保.燃油分级比对LESS燃烧室压力振荡频率的影响[J].航空动力学报,2015,30(6):1337-1343. |
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| 作者姓名： | 秦皓 汤冠琼 林宇震 李继保 |
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| 作者单位： | 北京航空航天大学 能源与动力工程学院 航空发动机气动热力国家级重点实验室, 北京 100191,北京航空航天大学 能源与动力工程学院 航空发动机气动热力国家级重点实验室, 北京 100191,北京航空航天大学 能源与动力工程学院 航空发动机气动热力国家级重点实验室, 北京 100191,中国航空工业集团公司 商用航空发动机有限责任公司, 上海 200241 |
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| 摘 要： | 实验研究了燃油分级比对low emissions with stirred swirls(LESS)燃烧室压力振荡频率的影响,在燃烧室进口压力为1.14~2.77MPa,燃烧室进口温度为645~808K,总油气比为0.0242~0.0303,燃烧室压降为3.14%~3.64%范围内,随着燃油分级比减小(32.7%降到5.21%),压力振荡频率下降.采用了简单均匀介质直管道模型和CFD数值方法分析燃油分级比对压力振荡频率的影响.结果表明:燃油分级比引起火焰区的起始位置、轴向长度和平均温度的变化是导致压力振荡频率变化的主要原因.
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| 关 键 词： | 压力振荡频率 燃油分级比 声学模型 低排放燃烧 燃烧室 |
| 收稿时间： | 2013/12/1 0:00:00 |
Influence of fuel stage ratio on pressure oscillation frequency of LESS combustor |
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| QIN Hao,TANG Guan-qiong,LIN Yu-zhen and LI Ji-bao.Influence of fuel stage ratio on pressure oscillation frequency of LESS combustor[J].Journal of Aerospace Power,2015,30(6):1337-1343. |
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| Authors: | QIN Hao TANG Guan-qiong LIN Yu-zhen and LI Ji-bao |
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| Institution: | National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China,National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China,National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China and Commercial Aircraft Engine Company Limited, Aviation Industry Corporation of China, Shanghai 200241, China |
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| Abstract: | Influence of fuel stage ratio on pressure oscillation frequency of low emissions with stirred swirls (LESS) combustor was tested. The pressure oscillation frequency dropped with the decrease of fuel stage ratio (from 32.7% to 5.21%) under the combustor inlet pressure of 1.14MPa to 2.77MPa, combustor inlet temperature of 645K to 808K, total fuel air ratio of 0.0242 to 0.0303 and combustor pressure drop of 3.14% to 3.64%. A homogeneous straight pipe model and CFD numerical method were adopted to analyze the influence of fuel stage ratio on pressure oscillation frequency. The results show that changes of original position, axial length and mean temperature of flame zone caused by fuel stage ratio are the main reasons contributing to the changes of pressure oscillation frequency. |
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| Keywords: | pressure oscillation frequency fuel stage ratio acoustic model low emission combustion combustor |
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