针栓结构参数对液氧/甲烷发动机跨临界燃烧效率的影响

谭天军; 张斌; 李志强; 向纪鑫; 徐吉峰; 任和; 郑晓霞

doi:10.13224/j.cnki.jasp.20220825

针栓结构参数对液氧/甲烷发动机跨临界燃烧效率的影响

doi: 10.13224/j.cnki.jasp.20220825

谭天军¹,
张斌²,
李志强^{1, 3},
向纪鑫^3,*, ,,
徐吉峰^{3, 4},
任和^{3, 5},
郑晓霞³

1.
太原理工大学机械与运载工程学院，太原 030024
2.
中国人民解放军空军装备部太原军事代表处，太原 030000
3.
太原理工大学航空航天学院，太原 030600
4.
中国商用飞机有限责任公司北京民用飞机技术研究中心，北京 102211
5.
中国商用飞机有限责任公司营销中心，上海 200126

基金项目: 山西省应用基础研究计划面上青年项目（20210302124681，20210302124385）；山西省高等学校科技创新项目（2021L069）；山西省关键核心技术和共性技术研发攻关专项（2020XXX017）；山西省科技重大专项（202101120401007）

详细信息

作者简介:
谭天军（1998-），男，硕士生，主要从事发动机跨临界燃烧方面的研究

通讯作者:
向纪鑫（1991-），男，讲师，博士，主要从事液体火箭发动机热防护方面的研究。E-mail：xiangjixin@tyut.edu.cn

中图分类号: V434.13
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- 文章访问数: 18
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- 被引次数: 0
出版历程
- 收稿日期: 2022-10-31
- 网络出版日期: 2023-12-21

Structural parameters of pintle on transcritical combustion efficiency of liquid oxygen/methane engine

TAN Tianjun¹,
ZHANG Bin²,
LI Zhiqiang^{1, 3},
XIANG Jixin^{3,*
, ,},
XU Jifeng^{3, 4},
REN He^{3, 5},
ZHENG Xiaoxia³

1.
College of Mechanical and Vehicle Engineering，Taiyuan University of Technology，Taiyuan 030024，China
2.
Military Representative Office in Taiyuan，Air Force Equipment Department of the Chinese People’s Liberation Amry，Taiyuan 030000，China
3.
College of Aeronautics and Astronautics，Taiyuan University of Technology，Taiyuan 030600，China
4.
Beijing Aircraft Technology Research Institute，Commercial Aircraft Corporation of China， Ltd.，Beijing 102211，China
5.
Marketing Center，Commercial Aircraft Corporation of China， Ltd.，Shanghai 200126，China

摘要

摘要:
为了研究跨临界燃烧下针栓结构参数对燃烧效率的影响，采用标准k-ε湍流模型、非绝热稳态扩散火焰面模型，同时考虑流体真实物性，对液氧/甲烷针栓式发动机跨临界燃烧进行数值研究。分析不同物性计算方法对推力室内流场影响，并分析针栓喷注器径向环缝宽度、轴向环缝宽度对发动机燃烧效率的影响。结果表明：考虑跨临界效应时，形成的中心回流区和高温区域均较小。在一定范围内，径向环缝增大，燃烧效率先减小后增大，轴向环缝宽度增大，燃烧效率降低，轴向环缝宽度取较小值而径向环缝宽度取较大值时，可获得较高的燃烧效率。动量比小于1时，增大轴向动量可有效改善混合；动量比大于1时，增大轴向动量对改善混合的作用减弱。燃烧效率随动量比增大而降低，当不同工况的动量比值接近时，总动量较大工况的燃烧效率更高。
- 液氧/甲烷火箭发动机 /
- 针栓式喷注器 /
- 跨临界燃烧 /
- 结构参数 /
- 燃烧效率
Abstract:
To study the effects of pintle structural parameters on the combustion efficiency in transcritical combustion, a standard k-ε turbulence model and a non-adiabatic stable diffusion flamelet model were utilized to numerically study the transcritical combustion of an LOX/CH₄ pintle engine considering the real gas properties of fluid. The study analyzed the impact of various methods for calculating physical properties on the flow field within the thrust chamber, and the effects of radial and axial annular seam width of pintle injector on engine combustion efficiency were analyzed. The results showed that the size of both the central recirculation zone and the high temperature zone was reduced when considering the transcritical effect. Within a certain range, as the radial annular seam width increased, the combustion efficiency initially decreased and then increased, as the axial annular seam width increased, the combustion efficiency decreased. A greater combustion efficiency can be achieved by reducing the axial annular seam width and increasing the radial annular seam width. When the total momentum ratio was less than 1, increasing axial momentum can effectively improve mixing. However, if the total momentum ratio was greater than 1, increasing axial momentum can hinder the improvement of mixing. The combustion efficiency decreased with the increase of the total momentum ratio. When the total momentum ratio for different operating conditions was similar, the operating condition with a higher momentum ratio exhibited a higher combustion efficiency.
- LOX/CH₄ rocket engine /
- pintle injectors /
- transcritical combustion /
- structural parameters /
- combustion efficiency

HTML

图 1 推力室结构示意图

Figure 1. Schematic diagram of thrust chamber

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图 2 纯流体相图

Figure 2. Pure fluid phase diagram

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图 3 推力室压力为8 MPa时氧气预测热物性和NIST数据比较

Figure 3. Comparison of NIST data and predicted thermodynamic properties for oxygen at thrust chamber pressure 8 MPa

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图 4 推力室头部计算域网格

Figure 4. Computation grid of thrust chamber head

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图 5 计算域边界条件

Figure 5. Boundary conditions of computational domain

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图 6 实验结果和数值结果比较

Figure 6. Comparison of simulation results with test data

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图 7 不同物性计算方程时轴向上压力分布

Figure 7. Pressure distribution of axis at different physical property calculation equations

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图 8 不同物性计算方程时温度分布

Figure 8. Temperature distribution at different physical property calculation equations

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图 9 不同物性计算方程时推力室头部速度流线

Figure 9. Velocity streamlines of thrust chamber head at different physical property calculation equations

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图 10 压力提取位置

Figure 10. Extract the position of pressure

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图 11 不同h_r时燃烧效率

Figure 11. Combustion efficiency at different h_r

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图 12 不同h_r时T_mr

Figure 12. T_mr at different h_r

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图 13 当h_a= 0.7 mm时推力室头部流线图

Figure 13. Streamlines of thrust chamber head at h_a=0.7 mm

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图 14 当h_a=0.7 mm时温度云图

Figure 14. Temperature distribution at h_a=0.7 mm

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图 15 不同h_a时燃烧效率

Figure 15. Combustion efficiency at different h_a

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图 16 不同h_a时T_mr

Figure 16. T_mr at different h_a

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图 17 不同h_a和h_r时推力室头部流线图

Figure 17. Streamlines of thrust chamber head at different h_a and h_r

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图 18 不同h_a和h_r时温度云图

Figure 18. Temperature distribution at different h_a and h_r

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图 19 不同h_r时T_mr和η关系

Figure 19. Relationship between T_mr and η at different h_r

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图 20 不同h_r时T_m和η关系

Figure 20. Relationship between T_m and η at different h_r

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表 1 G2案例测试条件

Table 1. Test condition for the G2 case

压力/MPa	组分	温度/K	质量流量/（kg/s）
5.6	CH₄	288	0.1431
5.6	O₂	85	0.0444

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表 2 不同网格数时压力和温度

Table 2. Pressure and temperature of different grids

网格数/10⁴	参数	X/mm
网格数/10⁴	参数	50	100	150	200
5	T/K	1450.58	1707.49	2022.02	2392.32
	σ_T/%	1.734	0.745	0.724	1.425
	p/MPa	6.946	6.919	6.880	6.843
	σ_p/%	0.872	0.847	0.811	0.803
10	T/K	1403.28	1706.19	2022.08	2375.68
	σ_T/%	−1.583	0.668	0.728	0.720
	p/MPa	6.912	6.885	6.849	6.812
	σ_p/%	0.375	0.359	0.353	0.357
15	T/K	1425.85	1694.87	2007.47	2358.70
15	p/MPa	6.886	6.861	6.824	6.788

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