中心分级环形燃烧室液雾点熄火边界试验

王智辉; 张弛; 甘志超; 高安雯; 韩啸; 陶雯婕

doi:10.13700/j.bh.1001-5965.2023.0352

中心分级环形燃烧室液雾点熄火边界试验

doi: 10.13700/j.bh.1001-5965.2023.0352

王智辉^{1, 2, 3},
张弛^{1, 2, 3},
甘志超^{1, 2, 3},
高安雯^{1, 2, 3},
韩啸^{1, 2, 3, ,},
陶雯婕⁴

1.
北京航空航天大学航空发动机研究院，北京 102206
2.
北京航空航天大学航空发动机气动热力国家级重点实验室，北京 102206
3.
北京航空航天大学先进航空发动机协同创新中心，北京 102206
4.
中国航发商用航空发动机有限责任公司，上海 200241

基金项目:

中央高校基本科研业务费专项资金；国家自然科学基金(52106128)

详细信息

通讯作者:
E-mail：han_xiao@buaa.edu.cn

中图分类号: V231.2
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- 文章访问数: 217
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- 被引次数: 0
出版历程
- 收稿日期: 2023-06-13
- 录用日期: 2023-07-21
- 网络出版日期: 2023-08-16
- 整期出版日期: 2025-06-30

Spray ignition and blow-out boundary of centrally staged annular combustor

WANG Zhihui^{1, 2, 3},
ZHANG Chi^{1, 2, 3},
GAN Zhichao^{1, 2, 3},
GAO Anwen^{1, 2, 3},
HAN Xiao^{1, 2, 3
, ,},
TAO Wenjie⁴

1.
Research Institute of Aero-Engine，Beihang University，Beijing 102206，China
2.
National Key Laboratory of Science and Technology on Aero-Engine Aerothermodynamics，Beihang University，Beijing 102206，China
3.
Collaborative Innovation Center for Advanced Aero-Engine，Beihang University，Beijing 102206，China
4.
AECC Commercial Aircraft Engine Co.，Ltd.，Shanghai 200241，China

Funds:

The Fundamental Research Funds for the Central Universities; National Natural Science Foundation of China (52106128)

More Information

Corresponding author: E-mail：han_xiao@buaa.edu.cn

摘要

摘要:
针对中心分级环形燃烧室液雾点熄火问题，对环形模型燃烧室进行了试验研究。在由16个中心分级燃烧室头部组成的环形模型燃烧室中，在常温常压条件下，对航空煤油RP-3的液雾点熄火过程进行了试验研究。试验测试了该环形燃烧室的点火和熄火边界，获得了贫油点火和熄火边界曲线。在燃烧室压降0.5%～3%范围内，随着压降增大，点火边界油气比呈先降低后升高的趋势，熄火边界油气比随压降增大逐渐降低后基本保持恒定。研究结果表明：通过在燃烧室头部安装导流环能够有效降低环形燃烧室贫油点火边界。使用单反相机记录了环形燃烧室点火和熄火过程，不同压降下的火焰周向传播相似，火焰传播存在周向不对称性，头部熄火顺序则与燃油均匀性相关。
- 环形燃烧室 /
- 中心分级 /
- 液雾火焰 /
- 点火 /
- 熄火
Abstract:
An experimental study of an annular model combustor was conducted to investigate spray ignition and blow-out problems in a centrally staged annular combustor. In the annular model combustor composed of 16 centrally staged injectors, the spray ignition and blow-out process of aviation kerosene RP-3 was experimentally studied under atmospheric temperature and pressure. Within the range of 0.5%–3% of the pressure drop in the combustor, with the increase in the pressure drop, the fuel-air ratio of the ignition boundary first decreases and then increases, while the fuel-air ratio of the blow-out boundary gradually decreases and then remains constant. The research results show that the lean oil ignition boundary of the annular combustor can be significantly improved by installing the flow deflector at the injectors. The ignition and blow-out process of the annular combustor is recorded with a digital single lens reflex. The circumferential propagation of flame is similar under different pressure drops, and the flame propagation is circumferential asymmetry. The blow-out sequence of the injector is related to the fuel uniformity.
- annular combustor /
- centrally staged /
- spray flame /
- ignition /
- blow-out

HTML全文

图 1 单头部中心分级结构

Figure 1. Single-injector centrally staged structure

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图 2 中心分级环形燃烧室（安装导流环）

Figure 2. Centrally staged annular combustor (with flow deflector)

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图 3 环形燃烧室试验系统

Figure 3. Test system for annular combustor

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图 4 旋流器有效面积标定结果

Figure 4. Calibration results of effective area of swirlers

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图 5 喷嘴均匀性标定结果

Figure 5. Calibration results of nozzle uniformity

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图 6 中心分级环形燃烧室火焰图像（无导流环）

Figure 6. Flame image of centrally staged annular combustor (without flow deflector)

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图 7 环形燃烧室点火边界

Figure 7. Ignition boundary of annular combustor

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图 8 导流环作用机理

Figure 8. Mechanism of flow deflector

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图 9 导流环作用数值计算结果^[19]

Figure 9. Numerical calculation results of flow deflector effect ^[19]

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图 10 环形燃烧室熄火边界

Figure 10. Blow-out boundary of annular combustor

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图 11 预燃级熄火当量比

Figure 11. Blow-out equivalence ratio of pilot stage

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图 12 环形燃烧室火焰周向传播不对称性

Figure 12. Circumferential propagation asymmetry of flame in annular combustor

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图 13 燃烧室熄火过程

Figure 13. Blow-out process of annular combustor

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