喷嘴结构和射流参数对射流预冷温度特性的影响

冯爽; 李宝宽; 杨晓晰; 扈鹏飞

doi:10.13224/j.cnki.jasp.20210566

喷嘴结构和射流参数对射流预冷温度特性的影响

doi: 10.13224/j.cnki.jasp.20210566

冯爽^1,,
李宝宽^1,*, ,,
杨晓晰¹,
扈鹏飞²

1.
东北大学冶金学院热能工程系，沈阳 110819
2.
中国航发沈阳发动机研究所，沈阳 110015

基金项目: 中央高校基本科研业务费专项基金（N2025013）

详细信息

作者简介:
冯爽（1997-），女，硕士生，研究领域为多相流热物理。E-mail：1901577@stu.neu.edu.cn

通讯作者:
李宝宽（1963-），男，教授、博士生导师，博士，研究领域为多相流热物理。E-mail：libk@mail.neu.edu.cn

中图分类号: V236
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- 被引次数: 0
出版历程
- 收稿日期: 2021-10-09
- 网络出版日期: 2023-12-28

Effect of nozzle structure and jet parameters on the temperature characteristics of mass injection and pre-compressor cooling

1.
Department of Thermal Engineering，School of Metallurgy，Northeastern University，Shenyang 110819，China
2.
Shenyang Engine Research Institute，Aero Engine Corporation of China，Shenyang 110015，China

摘要

摘要:
航空发动机进气温度过高是限制其性能的关键问题之一，采用射流预冷技术可以有效降低航空发动机进气温度。为了研究射流预冷技术对进气道内温度场的影响，基于欧拉-拉格朗日方法，建立航空发动机进气道液滴雾化和蒸发过程的数学模型，实现气液两相的双向耦合，描述了射流预冷过程。并与已有的试验结果进行对比，验证了数学模型的准确性。并利用该数学模型研究了水气比、喷射速度、液滴粒径和喷嘴锥角对进气道降温效果和温度畸变的影响。结果表明：改变水气比发动机进气温度变化最显著，当水气比由0.02增大至0.055时，温降系数由8.10%增加到19.87%，蒸发率由85.76%降低为79.80%；当水气比为0.055、喷射速度为10 m/s、液滴粒径为25 μm和喷嘴锥角为15°时，温降系数最大为22.77%；增大喷嘴锥角和减小喷射速度会使进气道出口截面温度场分布更均匀。
- 射流预冷 /
- 温度畸变 /
- 雾化 /
- 蒸发 /
- 高温进气
Abstract:
Excessive high intake temperature is one of the key problems limiting the performance of aero-engines, mass injection and pre-compressor cooling (MIPCC) technology can effectively reduce the intake temperature of aero-engine. In order to investigate the influence of MIPCC technology on the temperature field in the inlet, a mathematical model of the droplet atomization and evaporation process was established. Based on Euler-Lagrange method, the mathematical model was used to realize the two-way coupling of the gas-liquid two-phase and describe the MIPCC process in the intake port of an aero-engine. Compared with the existing test results, the accuracy of the mathematical model was verified. The effects of water-air ratio, injection velocity, particle diameter and nozzle cone angle on the cooling effect and temperature distribution of the inlet were studied by using the mathematical model. The results showed that when the water-air ratio increased from 0.02 to 0.055, the cooling ratio increased from 8.10% to 19.87%, and the evaporation rate decreased from 85.76% to 79.80%; when the water-air ratio was 0.055, the injection velocity was 10 m/s, the droplet size was 25 μm and the nozzle cone angle was 15°, the maximum temperature drop coefficient was 22.77%. Increasing the nozzle cone angle and decreasing the injection velocity made the temperature field distribution in the outlet section of the inlet more uniform.
- mass injection and pre-compressor cooling /
- temperature distortion /
- atomization /
- evaporation /
- heigh-temperature inlet air

HTML

图 1 物理模型及网格划分

Figure 1. Physical model and grid division

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图 2 不同网格数量在3D截面处的温度分布

Figure 2. Temperature distribution at 3D cross-section with different grid quantities

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图 3 网格无关性验证

Figure 3. Grid independence verification

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图 4 不同截面试验温度和模拟温度的比较

Figure 4. Comparison of test and simulated temperatures for different cross-sections

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图 5 不同水气比下进气道中截面温度分布云图

Figure 5. Cloud map of cross-sectional temperature distribution in the intake duct under different water to air ratios

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图 6 不同水气比下不同截面的平均温度对比图

Figure 6. Comparison of average temperature at different cross-sections under different water to air ratios

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图 7 不同水气比下蒸发特性的变化图

Figure 7. Changes in evaporation characteristics under different water to air ratios

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图 8 不同流速下出口截面的温度畸变分析图

Figure 8. Analysis of temperature distortion at outlet cross-section under different flow velocities

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图 9 不同流速下进气道中截面温度分布云图

Figure 9. Cloud map of cross-sectional temperature distribution in the intake duct at different flow velocities

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图 10 不同流速下不同截面的平均温度对比图

Figure 10. Comparison of average temperature at different cross-sections under different flow rates

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图 11 不同流速下出口截面的温度畸变分析

Figure 11. Temperature distortion analysis of outlet section under different flow velocities

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图 12 不同粒径下进气道中截面的温度分布云图

Figure 12. Temperature distribution cloud map of the cross-section in the intake duct under different particle sizes

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图 13 不同粒径下不同截面的平均温度对比图

Figure 13. Comparison of average temperature at different cross-sections under different particle sizes

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图 14 不同粒径不同截面的蒸发量

Figure 14. Evaporation of different particle sizes and cross-sections

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图 15 不同粒径下液滴分布和各截面温度分布

Figure 15. Droplet distribution and temperature distribution at different cross-sections under different particle sizes

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图 16 不同粒径下出口截面的温度畸变分析

Figure 16. Temperature distortion analysis of outlet cross-section under different particle sizes

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图 17 不同喷嘴锥角下进气道中截面的温度分布云图

Figure 17. Temperature distribution cloud map of the cross-section in the intake duct at different nozzle cone angles

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图 18 不同喷嘴锥角下出口截面的温度畸变分析

Figure 18. Temperature distortion analysis of outlet cross-section under different nozzle cone angles

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