Experimental and simulation study of aeroengine combustor based on CARS technology and UFPV approach
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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。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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Key words:
- aeroengine combustor /
- two-phase combustion /
- UFPV approach /
- CARS technology
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图 2 航空发动机燃烧室测量平台照片
Figure 2. Photograph of the aeroengine combustor measuring platform
图 4 CARS测量集成系统
Figure 4. Picture of CARS test integration system for aeroengine combustor
图 5 航空发动机主燃孔附近CARS测温位置示意图
Figure 5. Schematic diagram for CARS measurement location of temperature in the zone near the primary air jet holes
图 7 最大温度随当量标量耗散率变化的S型曲线
Figure 7. S curve of the maximum temperature with the variation of the stoichiometric scalar dissipation rate
图 8 当量标量耗散率为100s-1时，温度在混合分数空间的分布
Figure 8. Distribution of temperature T in the mixture fraction space when the stoichiometric scalar dissipation rate is 100s-1
图 9 燃料质量分数为0.015的等值面图
Figure 9. Iso-surface of liquid particle axis velocity is 5m/s (red surface) and -1m/s (blue surface) respectively
图 10 燃料质量分数为0.015的等值面图
Figure 10. Iso-surface distribution of fuel mass fraction of 0.015
图 12 燃烧室混合分数及燃油液滴直径分布
Figure 12. Mixture fraction and diameter of fuel droplets in combustor
表 1 Boundary inlet condition of combustor
Table 1. Boundary inlet condition of combustor
Flow rate of fuel/(kg·s-1) Flow rate of air/(kg·s-1) Excess air coefficient Inlet total temperature/K Inlet total pressure/MPa 0.0115 0.440 2.6 861 0.55 
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表 2 Temperature of the CARS technology measurements and numerical simulation
Table 2. Temperature of the CARS technology measurements and numerical simulation
Position CARS measured value/K Simulation value/K Error/% 1 2350 2263 -3.70 2 2300 2281 -0.08 3 1915 1951 1.88 4 1896 1936 2.11 5 1870 1772 -5.24 6 1907 1768 -7.29 7 2235 2258 1.03 8 2188 2255 3.00 9 2135 2168 1.54 10 2100 2165 3.10
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