旋流波瓣混合器对ATR燃烧室的特性影响研究

宋权斌; 肖和波; 李新卓; 王张翔; 常薛峰; 胡斌

doi:10.13224/j.cnki.jasp.20240007

旋流波瓣混合器对ATR燃烧室的特性影响研究

doi: 10.13224/j.cnki.jasp.20240007

1.
长沙理工大学能源与动力工程学院，长沙 410114
2.
中国科学院工程热物理研究所，北京 100190

基金项目: 长沙理工大学研究生科研创新项目（CSLGCX23077）

详细信息

作者简介:
宋权斌（1973-），男，副研究员，博士，主要从事燃气轮机燃烧室设计、数值模拟和试验方面的研究。E-mail：sqb@csust.edu.cn

通讯作者:
李新卓（1991-），男，讲师，博士，主要从事计算流体力学及清洁燃烧技术方面的研究。E-mail：Leesin1949@csust.edu.cn

中图分类号: V236
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出版历程
- 收稿日期: 2024-01-03
- 网络出版日期: 2024-09-16

Study on influence of swirl lobe mixer on ATR combustor characteristics

1.
College of Energy and Power Engineering，Changsha University of Science and Technology，Changsha 410114，China
2.
Institute of Engineering Thermophysics，Chinese Academy of Sciences，Beijing 100190，China

摘要

摘要:
旋流波瓣混合器可以促进空气涡轮火箭（ATR）燃烧室内空气与富燃燃气的高效混合，提升发动机燃烧室燃烧效率。基于发动机地面工况下燃烧室进口参数，通过数值模拟的方法，对比了4种波瓣旋转角度（0°、3°、5°、7°）对燃烧室波瓣尾缘涡量和温度分布的影响，从燃烧效率、压力损失和热混合效率3个方面对不同波瓣旋转角度下的发动机性能进行了分析。研究结果表明：波瓣进行旋转可以增强流向涡强度，促进热混合效率提升，波瓣旋转角度为5°时热混合效率提升了1.2%；波瓣旋转角度为5°时的燃烧效率最高，出口燃烧效率比常规波瓣混合器提升了3.35%；燃烧室总压损失主要由燃烧反应引起，波瓣旋转会增强燃烧效果，并一定程度增大压力损失。
- 小型空气涡轮火箭（ATR）发动机 /
- 旋流波瓣混合器 /
- 非预混燃烧 /
- 流向涡 /
- 燃烧效率
Abstract:
The swirl lobe mixer can promote efficient mixing of air and fuel-rich gas in the combustion chamber of the air-turbo-rocket (ATR) and improve the combustion efficiency of the engine combustion chamber. Based on combustion chamber inlet parameters under engine ground conditions, the effects of four lobe rotation angles (0°, 3°, 5°, 7°) on the vortex and temperature distribution at the tail edge of combustion chamber lobes were compared by numerical simulation, and the engine performance under different lobe rotation angles was analyzed from three aspects: combustion efficiency, pressure loss and hot mixing efficiency. The results showed that lobe rotation can enhance the flow vortex intensity and promote the thermal mixing efficiency. When the lobe rotation angle was 5°, the thermal mixing efficiency increased by 1.2%. The combustion efficiency was the highest when the lobe rotation angle was 5°, and the combustion efficiency at the outlet was 3.35% higher than that of the conventional lobe mixer. The total pressure loss of the combustion chamber was mainly caused by the combustion reaction, and the lobe rotation could enhance the combustion effect and increase the pressure loss to a certain extent.
- small air-turbo-rocket (ATR) engine /
- swirl lobe mixer /
- non-premixed combustion /
- streamwise vorticities /
- combustion efficiency

HTML

图 1 波瓣混合器诱导流向涡旋示意图^[11]

Figure 1. Diagram of vortex induced by lobe mixer^[11]

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图 2 小型ATR燃烧室示意图及计算域（单位：mm）

Figure 2. Schematic diagram and computational domain of the small ATR combustor （unit：mm）

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图 3 波瓣混合器模型

Figure 3. Lobe mixer model

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图 4 网格及局部放大

Figure 4. Mesh and local magnification

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图 5 网格无关性验证

Figure 5. Validation of grid independence

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图 6 实验与CFD最大涡量分布对比^[16]

Figure 6. Comparison of maximum vorticities distribution between experiment and CFD^[16]

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图 7 当量比为0.7条件下CFM56燃烧室中心线温度分布^[38]

Figure 7. Temperature distribution along the centerline of the CFM56 combustor under ϕ=0.7 condition^[38]

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图 8 不同截面流向涡云图

Figure 8. Streamwise vortex contours at different cross sections

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图 9 不同波瓣流向涡沿程分布

Figure 9. Streamwise vorticities distribution with different lobes

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图 10 不同截面温度云图

Figure 10. Temperature contours at different cross planes

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图 11 热混合效率沿程分布

Figure 11. Thermal mixing efficiency distribution

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图 12 总压恢复系数分布

Figure 12. Total pressure recovery coefficient distribution

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图 13 CO摩尔分数分布

Figure 13. CO mole fraction distribution

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图 14 燃烧效率分布图

Figure 14. Combustion efficiency distribution

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表 1 旋流波瓣混合器的主要参数

Table 1. Main parameters of the swirl lobed mixers

波瓣混合器编号旋转角度γ/（°）

A 0

B 3

C 5

D 7

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表 2 富燃燃气组分及摩尔分数

Table 2. Composition and mole fraction of fuel-rich gas

组分摩尔分数

CO 0.42

H₂ 0.41

C 0.04

N₂ 0.10

CH₄ 0.03

下载: 导出CSV

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