AUTO-IGNITION TABULATED METHOD FOR SUPERSONIC COMBUSTION AT HIGH MACH NUMBER
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摘要: 超燃冲压发动机燃烧室工作在高马赫数工况时, 入口来流空气的总焓非常高, 自点火在高焓条件下成为维持火焰稳定的重要物理化学过程. 本文借鉴火焰面/进度变量模型的降维思路, 发展了一种基于化学动力学的自点火建表方法. 通过定义混合分数和进度变量将复杂多维的化学反应降维, 并成功将数据库方法结合到现有的大涡模拟求解器中. 经过测试和验证, 该方法初步具备对超声速自点火燃烧进行仿真描述的能力. 针对自点火诱导的超声速燃烧问题开展数值模拟, 该方法通过查表的方式有效降低了化学反应求解过程中的计算量. 在采用详细化学反应机理时能够准确地再现自点火行为和火焰结构, 并且预测的温度和重要组分分布与实验吻合较好.Abstract: When the scramjet combustor works under high Mach number conditions, the total enthalpy of the inlet air is very high, and auto-ignition becomes an important physical and chemical process to maintain flame stability. This paper develops an auto-ignition tabulated method based on chemical kinetics, referring to the dimensions reduction means of the flamelet/progress variable model. The complex and multi-dimensional chemical reactions is reduced by defining the mixture fraction and progress variables, and the database method is successfully integrated into the existing large eddy simulation solver. After testing and verification, the method possesses the ability to simulate and describe the supersonic auto-ignition and flame. Numerical simulation is carried out for supersonic combustion induced by auto-ignition in two configuration. This method effectively reduces the amount of calculation in the process of solving chemical reactions by looking up the database. When the detailed chemical reaction mechanism is used, the auto-ignition behavior and flame structure can be accurately reproduced, and the predicted temperature and the distribution of important components are in good agreement with the experiment.
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Key words:
- auto-ignition /
- supersonic combustion /
- tabulated method /
- high enthalpy
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图 1 化学反应动力学计算出的温度和H2曲线
Figure 1. Temperature and H2 curves calculated by chemical reaction kinetics
图 4 OH基质量分数和温度随进度变量的变化
Figure 4. Variation of OH mass fraction and temperature with progress variables
图 5 H2反应速率和进度变量生成率变化曲线
Figure 5. H2 generation rate and progress variable generation rate curve
图 6 数据库查表插值示意图
Figure 6. Schematic diagram of lookup and interpolation from the auto-ignition database
图 8 组分H2和H2O质量分数在反应中的变化
Figure 8. Variation of H2 and H2O mass fraction in the reaction
图 9 不同初始温度下温度随时间变化
Figure 9. Temperature variation with time at different initial temperatures
图 10 Gamba实验构型计算域示意图 (单位: mm)
Figure 10. Schematic diagram of the computational domain of the Gamba’s experiments (unit: mm)
图 12 Burrows–Kurkov实验构型计算域示意图 (单位: mm)
Figure 12. Schematic diagram of the computational domain of the Burrows–Kurkov experimental configuration (unit: mm)
图 13 中心截面上温度和OH基的分布
Figure 13. Distributions of temperature and mass fration of OH at the central slice
图 14 出口位置(x = 356 mm)总温剖面
Figure 14. Total temperature profile at the outlet (x = 356 mm)
表 1 初始参数的范围和取值
Table 1. Range and value of control parameters
Parameter Range N Value Z 0~1 35 $ \lg ({i_Z} + 1)/\lg 16 \times 0.0283 $, $ 1 \leqslant {i_Z} \leqslant 15 $ $0.0283 + {2^{(i - 15)/2}}/{2^{10}} \times 0.9727,$ $ 16 \leqslant {i_Z} \leqslant 35 $ p/MPa 0.05~1 20 0.05ip T0/K 850~1550 30 850 + 20iT 
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表 2 Burrows–Kurkov实验射流和来流参数
Table 2. Jet and inflow parameters in Burrows–Kurkov experiment
Parameter Jet Inflow Ma 2.4 1 T/K 1237.9 261.7 p/Pa 96000.0 114465.5 $ {Y_{\rm{O_2}}} $ 0.258 0.0 $ {Y_{\rm{H_2}O}} $ 0.256 0.0 $ {Y_{\rm{H_2}}} $ 0.0 1.0 $ {Y_{\rm{N_2}}} $ 0.486 0.0 Δ/mm 0.0075 0.0075
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