| 摘要: |
| 提出了描述航空发动机加力燃烧室内气相湍流燃烧的模型方程，并考虑了加力喷油效应。通过结合双时间尺度k－ε湍流模型、热通量高温辐射模型及SIMPLE方法，对实际运行的加力燃烧室内的湍流燃烧进行了数值模拟，得到了数值流场图及温度、组分浓度的等值线分布，给出了燃烧效率和总压恢复系数，数值解证明了湍流燃烧模型的可解性与合理性。 |
| 关键词: 航空发动机 加力燃烧室 湍流燃烧 湍流模型 |
| DOI： |
| 分类号:V231.2 |
| 基金项目:航空工业总公司资助 |
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| SINGLE PHASE COMBUSTION MODEL AND ITS APPLICATION IN A JET ENGINE AFTERBURNER |
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Zhu Zuojin,Han Bai,Chen Yiliang,Zhang Xiaochun
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1.Dept. of Thermal Science and Energy Engineering,China Univ. of Science and Technology, Hefei, 230026;2.Shenyang Aeroengine Research Inst, Shenyang, 110015
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| Abstract: |
| The turbulent combustion model in an aeroengine afterburner is presented. Moreattention is paid to the important effects of fuel injection in an afterburner. By employing the multipletime scale turbulent k-ε model, the high temperature heat flux radiation model and SIMPLEalgorithm, the numerical study of turbulent combustion process in a practical jet engine afterburner iscarried out, and the numerical velocity field, temperature and concentration contour distribution, theefficiency of burning and recovery coefficient of total pressure are obtained. The result indicates thatthere is a great solvability and reasonability with the presented turbulent combustion model. |
| Key words: Aircraft engine Afterburner Turbulent combustion Turbulence model |
