扣焓火焰面模型在喷雾燃烧模拟中的应用

何俊奕; 李峰; 胡群; 王利坡

doi:10.21656/1000-0887.440064

扣焓火焰面模型在喷雾燃烧模拟中的应用

doi: 10.21656/1000-0887.440064

何俊奕^1,,
李峰^2,,
胡群^1,,
王利坡^1, ,

1.
上海交通大学密西根学院，上海 200240
2.
北京动力机械研究所，北京 100074

(我刊编委王利坡来稿)

详细信息

作者简介:
何俊奕(1995—)，男，硕士(E-mail: damienhejunyi@sjtu.edu.cn)

李峰(1990—)，男，硕士(E-mail: 906309319@qq.com)

胡群(1997—)，男(E-mail: qun_hu@sjtu.edu.cn)

通讯作者:
王利坡(1974—)，男，副教授，博士，博士生导师(通讯作者. E-mail: Lipo.Wang@sjtu.edu.cn)

中图分类号: O357.41
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- 被引次数: 0
出版历程
- 收稿日期: 2023-03-10
- 修回日期: 2023-05-12
- 刊出日期: 2023-09-01

Application of Enthalpy Deficit Flamelet Model in Spray Combustion Simulation

HE Junyi^1
,,
LI Feng^2
,,
HU Qun^1
,,
WANG Lipo^{1
, ,}

1.
UM-SJTU Joint Institute, Shanghai Jiao Tong University, Shanghai 200240, P.R.China
2.
Beijing Power Machinery Research Institute, Beijing 100074, P.R.China

(Contributed by WANG Lipo, M. AMM Editorial Board)

摘要

摘要: 基于OpenFOAM的求解器，使用大涡模拟结合纯气相火焰面生成流形方法进行了喷雾燃烧模拟，并采用简单的扣焓处理来考虑蒸发热损失.该求解器首先借助悉尼乙醇喷雾火焰标模EtF7进行了验证.预测的气相平均温度和液滴统计数据与实验数据吻合良好，精度与喷雾火焰面模型接近.湍流-化学反应相互作用建模处理可能对模拟精度有更大影响.然后，对一个真实的航空发动机折流燃烧室进行了两组工况的数值模拟.仿真结果合理展现了两种工况下喷雾火焰燃烧的不同特征，并且预测的总压损失值接近于测量值.
- 喷雾燃烧 /
- 大涡模拟 /
- 火焰面生成流形 /
- 航空发动机折流燃烧室
Abstract: An OpenFOAM-based solver for spray combustion simulation with the large eddy simulation (LES) and the flamelet generated manifold (FGM) method, was developed. A simple reduction of the temperature was employed to account for the evaporative heat loss. The solver was firstly validated against the Sydney piloted ethanol spray flame benchmark EtF7. The predicted mean gas temperature and droplet statistics correspond well with the experimental data and have similar accuracy to the spray flamelet model. The turbulence-chemistry interaction modeling may have a larger influence on the simulation accuracy. Then a realistic gas turbine slinger combustor was simulated with 2 sets of operating conditions. The simulation results reveal different flame characteristics of the 2 working conditions. The predicted total pressure losses are close to the measured values.
- spray combustion /
- large eddy simulation /
- flamelet generated manifold /
- gas turbine slinger combustor
edited-by

edited-by
注释:

1) (我刊编委王利坡来稿)

HTML全文

图 1 FGM方法的实施流程

Figure 1. Procedures of FGM method

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图 2 悉尼喷雾燃烧室计算域及网格

Figure 2. The computation domain and mesh of the Sydney spray combustor

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图 3 中心线附近网格分布

Figure 3. Grid distribution near the centerline

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图 4 不同网格预测得到在轴向位置x/D=30处的气相平均温度T、液滴Sauter平均直径S_md和液滴轴向平均速度U_x的径向分布

Figure 4. Predicted radial profiles of mean gas temperature T, Sauter mean droplet diameter S_md and axial mean droplet velocity U_x at x/D=30 with different meshes

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图 5 y=0截面的瞬时和平均速度场、温度场、混合分数场

注为了解释图中的颜色，读者可以参考本文的电子网页版本，后同.

Figure 5. Instantaneous and mean velocity magnitude, temperature and mixture fraction distributions at section y=0

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图 6 预测气相平均温度与实验值在不同轴向位置的径向分布

Figure 6. Predicted radial profiles of the mean gas temperature with the experimental data in 3 different axial positions

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图 7 预测液滴S_md与实验值在不同轴向位置的径向分布

Figure 7. Predicted radial profiles of spray droplets S_md with the experimental data in 6 different axial positions

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图 8 预测液滴轴向平均速度与实验值在不同轴向位置的径向分布

Figure 8. Predicted radial profiles of the axial mean droplet velocity with the experimental data in 6 different axial positions

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图 9 实际折流燃烧室的计算域

Figure 9. The computation domain of the realistic slinger combustor

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图 10 计算域网格的局部几何细节

Figure 10. Local geometric details of the computation mesh

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图 11 y=0截面的预测瞬时速度分布和流线图

Figure 11. Predicted velocity distributions and streamlines at section y=0

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图 12 y=0截面的预测瞬时和平均总温分布

Figure 12. Predicted instantaneous and mean total temperature distributions at section y=0

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图 13 温度测量截面的预测瞬时和平均总温分布

Figure 13. Predicted instantaneous and mean total temperature distribution at temperature measurement section

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图 14 y=0截面的预测火焰指数分布

Figure 14. Predicted flame index distributions at section y=0

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表 1 液相引起的源项表达式

Table 1. Expressions of liquid source terms

source term	expression
S_ρ	$ -\frac{1}{V_c} \sum\limits_p \dot{m}_p N_p$
S_{u, i}	$ \frac{1}{V_c} \sum_p m_p N_p\left[\left(U_{p, i}^{t_n+\Delta t}-U_{p, i}^{t_n}\right) / \Delta t-g_i\right]-\frac{1}{V_c} \sum\limits_p \dot{m}_p N_p U_{p, i}^{t_n}$

下载: 导出CSV

表 2 两组不同工况的测量数据

Table 2. Measured data in 2 working conditions

index	working condition 1	working condition 2
air inlet mass flow rate ṁ_air/(kg·s^-1)	2.313	2.707
fuel inlet mass flow rate ṁ_fuel/(g·s^-1)	13.8	31.7
fuel air mass ratio (F/A)/%	0.596 6	1.171 7
air inlet temperature T_air/K	300	300
fuel inlet temperature T_fuel/K	300	300
air inlet total pressure P_{t, air}/kPa	305.103	408.172
total pressure loss ΔP_t/kPa	50.912	74.861

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表 3 进程变量源项在不同燃烧区域的条件均值

Table 3. Conditional means of progress variable source terms in different combustion zones

working condition	ω_Y/(kg·m^-3·s^-1)
working condition	ξ=-1	ξ=+1
working condition 1	5.03	4.44
working condition 2	13.82	7.03

下载: 导出CSV

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