生物航煤燃烧低压模化数值模拟

何彦潼; 邓甜; 王伟

doi:10.13700/j.bh.1001-5965.2023.0826

生物航煤燃烧低压模化数值模拟

doi: 10.13700/j.bh.1001-5965.2023.0826

何彦潼¹,
邓甜¹,
王伟^2, ,

1.
中国民航大学中欧航空工程师学院，天津 300300
2.
中国民航大学适航学院，天津 300300

基金项目:

天津市教委科研计划(2020KJ036)

详细信息

通讯作者:
E-mail：weiwangcauc@126.com

中图分类号: V231.21
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- 被引次数: 0
出版历程
- 收稿日期: 2023-12-20
- 录用日期: 2024-04-02
- 网络出版日期: 2024-04-10
- 整期出版日期: 2026-03-31

Numerical simulation of low-pressure modeling of bio-jet coal combustion

HE Yantong¹,
DENG Tian¹,
WANG Wei^{2
, ,}

1.
Sino-European Institute of Aviation Engineering，Civil Aviation University of China，Tianjin 300300，China
2.
School of Airworthiness，Civil Aviation University of China，Tianjin 300300，China

Funds:

Scientific Research Project of Tianjin Municipal Education Commission (2020KJ036)

More Information

Corresponding author: E-mail：weiwangcauc@126.com

摘要

摘要:
全球能源需求增长和环境污染加剧背景下，生物航煤作为清洁、低碳、可持续燃料，引领未来燃料发展。航空发动机燃烧室的原型试验受到实际条件限制，低压模化试验可简化工况参数，有效解决实际问题并满足工程需求。为此，以生物航煤为燃料，采用3种模化准则，对燃烧室进行低压模化数值模拟研究，并与原设计状态对比。结果表明：等容积流率模化准则（Q准则）预测的流场分布与原设计状态最接近，且轴向和切向温度场分布优于等燃烧效率模化准则（K准则）和L准则。低压模化条件下，与原设计状态相比，燃烧效率降低2%～3%。特别是当压力指数过高时，L准则模化后的燃油流量过小，不适用于航空发动机的模化试验。出口截面温度分布系数的预测结果显示，K准则的预测值与原设计值相比，存在负偏差，Q准则预测结果的平均误差最小。综合来看，Q准则为最优模化准则，其计算结果可为航空发动机燃烧室的低压模化试验研究提供参考。
- 航空发动机 /
- 低压模化 /
- 数值模拟 /
- Q准则 /
- 生物航煤
Abstract:
In the context of global energy demand growth and environmental pollution intensification, bio-jet coal as a clean, low-carbon, sustainable fuel, leading the future fuel development. The prototype test of an aero-engine combustion chamber is limited by practical conditions, while the low-pressure modeling test simplifies working parameters, effectively solves practical problems and meets engineering requirements. Three modeling criteria are used in this article’s low-pressure modeling numerical simulation of the combustor, which uses bio-jet as fuel. The results are compared to those computed in the original design condition. The results show that the flow field distribution predicted by the equal volume flow rate criterion (Q criterion) is the closest to the original design state, and the axial and tangential temperature field distribution is better than the equal combustion efficiency criterion (K criterion) and L criterion. Under the condition of low-pressure modeling, the combustion efficiency is reduced by 2% to 3% compared to the original design state. Especially when the pressure index is too high, the fuel flow after the L criterion is too small, and it is not suitable for aero-engine modeling test. The prediction results of the temperature distribution coefficient of the exit section show that the predicted value of the K criterion has a negative deviation compared with the original design value. The Q criterion has the smallest average error in predicting results. In conclusion, the Q criterion is the best modeling criterion, and the results of its computations can be used as a guide for the low-pressure modeling test of the combustion chamber of an aero engine.
- aero-engine /
- low-pressure modeling /
- numerical simulation /
- Q criterion /
- bio-jet coal

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图 1 燃烧室几何结构示意图

Figure 1. Schematic diagram of combustion chamber geometry

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图 2 计算网格

Figure 2. Computational grid

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图 3 不同网格数下轴向速度对比

Figure 3. Comparison of axial velocity at different mesh numbers

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图 4 不同网格数下温度对比

Figure 4. Comparison of temperature at different mesh numbers

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图 5 $ x $=10 mm截面处轴向速度模拟结果对比

Figure 5. Comparison of the simulation results of axial velocity at $ x $=10 mm cross-section

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图 6 $ x $=50 mm截面处轴向速度模拟结果对比

Figure 6. Comparison of the simulation results of axial velocity at $ x $=50 mm cross-section

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图 7 中心轴线上温度模拟结果对比

Figure 7. Comparison of temperature simulation results on the central axis

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图 8 原设计状态和不同模化状态的流场结构

Figure 8. Flow field structure of original design state and different modeling states

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图 9 原设计状态和不同模化状态的温度场分布

Figure 9. Temperature field distribution of original design state and different modeling states

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图 10 原设计状态和不同模化状态轴向切面$ x $=30 mm处的温度场分布对比

Figure 10. Comparison of temperature field distribution at axial section $ x $=30 mm between original design state and different modeling states

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图 11 原设计状态和不同模化状态轴向切面$ x $=70 mm处的温度场分布对比

Figure 11. Comparison of temperature field distribution at axial section $ x $=70 mm between original design state and different modeling states

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图 12 原设计状态和不同模化状态出口截面温度分布对比

Figure 12. Comparison of temperature distribution of exit section between original design state and different modeling states

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图 13 燃烧室出口温度沿高度的变化

Figure 13. Combustion chamber outlet temperature change with height

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表 1 原设计状态和不同模化准则下燃烧室的进口参数

Table 1. Inlet parameters of the combustion chamber in the design state and under different modeling criteria

状态	空气质量流量/ (kg·s⁻¹)	空气温度/K	空气压力/MPa	燃油质量流量/ 10⁻³(kg·s⁻¹)
原设计状态	1.3	800	2.5	17.95
Q准则	0.26	800	0.5	3.59
K准则	0.204	800	0.5	2.82
L准则	0.078	800	0.5	1.08

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表 2 生物航煤的基本性质^[22]

Table 2. Basic properties of bio-jet coal^[22]

密度/ (kg·m⁻³)	黏度/ (mm²·s⁻¹)	表面张力 (N·m⁻¹)	沸点/K	蒸发温度/K	气化潜热/ (kJ·kg⁻¹)	热值/ (MJ·kg⁻¹)
808	2.11	0.0236	477.95	311	252.6	44.4

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表 3 冷态条件计算模型

Table 3. Calculation model for cold conditions

模型算法				射流参数				边界条件（进口）
求解器	时间	湍流模型	近壁处理	进口类型	粒子类型	速度/(m·s⁻¹)	温度/K	总压/kPa	总温/K	湍流强度/%	水利直径/mm
隐式求解器	稳态	可实现k-ε模型	标准壁面函数	圆锥	液滴	30	300	110	300	5	34.56

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表 4 热态条件计算模型

Table 4. Calculation model for hot conditions

模型算法				射流参数				边界条件（进口）
求解器	燃烧模型	湍流模型	近壁处理	进口类型	粒子类型	速度/(m·s⁻¹)	温度/K	总压/MPa	总温/K	湍流强度/%	水利直径/mm
非稳态问题的隐式求解器	非预混PDF 燃烧模型	可实现k-ε模型	标准壁面函数	圆锥	液滴	30	400	2.5	800	5	34.56

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表 5 原设计状态和不同模化准则下燃烧室的出口参数

Table 5. Outlet parameters of combustion chamber under original design state and different modeling criteria

状态/准则	出口截面平均温度/K	出口截面最高温度/K	α_RTDF	β_OTDF
原设计状态	1289	1515	0.14	0.46
Q准则	1279	1577	0.16	0.62
K准则	1288	1456	0.10	0.34
L准则	1257	1506	0.21	0.55

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表 6 原设计状态和不同模化准则下的燃烧效率

Table 6. Combustion efficiency under original design state and different modeling criteria

状态/准则	燃烧效率
原设计状态	0.9768
Q准则	0.9553
K准则	0.9589
L准则	0.9478

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