| 采用CARS试验技术与UFPV数值方法研究航空发动机燃烧室 |
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| 作者姓名： | Xiong Moyou Le Jialing Huang Yuan Song Wenyan Yang Shunhua Zheng Zhonghua |
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| 作者单位： | 1.西北工业大学 动力与能源学院, 西安 710072 |
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| 基金项目： | Supported by NSFC91641205 |
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| 摘 要： | 在自主开发的软件平台上，采用基于URANS的方法计算航空发动机燃烧室的三维两相燃烧流动，考虑了液态燃油从液膜-液滴-燃气-燃烧的完整物理化学过程。其中，颗粒相采用LISA一次破碎模型，KH-RT二次破碎模型和标准的蒸发模型，湍流燃烧模型采用可以考虑非稳态燃烧特性的非稳态火焰面/反应进度变量方法，得到了航空发动机燃烧室中温度、组分浓度和燃油液滴的颗粒直径分布规律。同时，采用CARS光学手段测量燃烧室主燃区的温度分布，并将数值计算结果与光学试验测量值进行比较，数值计算结果和试验值吻合较好，数值计算误差小于7.3%。说明了本文的数值计算方法和UFPV方法在计算航空发动机燃烧室的两相燃烧流动时具有较高的精度。
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| 关 键 词： | 航空发动机燃烧室 两相燃烧 UFPV方法 CARS技术 |
| 收稿时间： | 2017-07-05 |
Experimental and simulation study of aeroengine combustor based on CARS technology and UFPV approach |
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| Xiong Moyou,Le Jialing,Huang Yuan,Song Wenyan,Yang Shunhua,Zheng Zhonghua.Experimental and simulation study of aeroengine combustor based on CARS technology and UFPV approach[J].Experiments and Measur in Fluid Mechanics,2017,31(5):15-23. |
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| Affiliation: | 1.School of Power and Energy, Northwestern Polytechnical University, Xi'an 710072, China2.Science and Technology on Scramjet Laboratory of Hypervelocity Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China |
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| Abstract: | Based on the Unsteady Reynolds Averaged Navier Stokes URANS) method, a three-dimensional two-phase turbulent combustion numerical software for aeroengine combustor has been developed. The physical and chemical processes taking place in the liquid fuel are simulated completely, including liquid film formation, breakup, evaporation and combustion. LISA and KH-RT are used as the primary and second atomization model respectively, and also the standard evaporation model is used to simulate the evaporation process. Besides, detailed chemical mechanism of kerosene is used for reaction kinetics, and the Unsteady Flamelet/Progress Variable (UFPV) approach in which the unstable combustion characteristics of the flame could be simulated is used as the combustion model. The temperature and species of the flow field and the diameter of fuel droplets in the aeroengine combustor are obtained. At the same time, the Coherent Anti-stokes Raman Scattering (CARS) technology is used to measure the temperature in the primary zone of the aeroengine combustor. Then the temperature of the simulation is compared with that measured by CARS technology, and the calculation error of numerical results is less than 7.3%. The studies have shown that the numerical method in this paper and UFPV approach can simulate the two-phase turbulent combustion process appropriately in the aeroengine combustor. |
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