射流预冷对航空发动机进气温度的特征性分析

冯爽; 李宝宽; 杨晓晰; 谢业平; 张海洋

doi:10.13224/j.cnki.jasp.20220131

射流预冷对航空发动机进气温度的特征性分析

doi: 10.13224/j.cnki.jasp.20220131

冯爽^1,,
李宝宽^1,*, ,,
杨晓晰¹,
谢业平²,
张海洋³

1.
东北大学热能工程系，沈阳 110819
2.
中国航发沈阳发动机研究所，沈阳 110015
3.
中国航发沈阳发动机研究所辽宁省航空发动机冲击动力学重点实验室，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，主要研究领域为多相流热物理。E-mail：475160225@qq.com

通讯作者:
李宝宽（1963-），男，教授、博士生导师，博士，主要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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- 文章访问数: 57
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- 被引次数: 0
出版历程
- 收稿日期: 2022-03-15
- 网络出版日期: 2023-10-17

Response surface characteristic analysis of jet precooling on aero-engine inlet temperature

1.
Department of Thermal Engineering，Northeastern University，Shenyang 110819，China
2.
Shenyang Engine Research Institute，Aero Engine Corporation of China，Shenyang 110015，China
3.
Liaoning Key Laboratory of Aeroengine Impact Dynamics，Shenyang Engine Research Institute，Aero Engine Corporation of China，Shenyang 110015，China

摘要

摘要:
为了研究射流预冷技术对预压段温度场的影响，采用欧拉-拉格朗日方法建立了液滴雾化蒸发过程的三维数学模型。气液两相之间的传质和动量交换是通过双向耦合的方法实现的。通过与已有试验结果的比较，验证了该数学模型的准确性。采用响应面法分析了水气比、喷射速度、液滴尺寸和喷嘴锥角对航空发动机进气温度的影响，建立了四因素三水平响应面法。结果表明：发动机进气空气温度的降温比为3.67%～26.02%。建立了基于多元回归方法的可视化非线性多变量设计优化方程，得到了水气比、喷射速度、液滴尺寸和喷嘴锥角对进气冷却效果的影响。当水气比为0.08、液滴尺寸为10.47 μm、喷射速度为39.52 m/s、喷嘴锥角为24.79°时，发动机最低预压缩冷却段温度为449.60 K。
- 射流预冷（MIPCC） /
- 响应面分析 /
- 数值模拟 /
- 雾化 /
- 蒸发
Abstract:
To investigate the influence of MIPCC technology on the temperature field in the pre-compressor section, a three-dimensional mathematical model was proposed to study the droplet atomization and evaporation process using the Eulerian-Lagrangian method. The mass transfer and momentum exchange between gas-liquid phase were realized by two-way coupling method. Compared with existing experimental results, the accuracy of the temperature in the mathematical model was verified. The effects of W-A ratio, velocity, particle size, and cone angle on the temperature of inlet air were analyzed by response surface methodology in the aero-engine, and a four-factor and three-level response surface methodology was established. The results showed that the temperature drop ratio of engine intake air temperature was 3.67%−26.02%. The visualized nonlinear multivariable design optimization equation based on multiple regression method and the effects of W-A ratio, velocity, particle size and cone angle on inlet cooling effect were obtained. When the W-A ratio was 0.08, the particle size was 10.47 μm, the velocity was 39.52 m/s and the cone angle was 24.79°, the minimum inlet temperature of aero-engine was 449.60 K.
- MIPCC /
- response surface analysis /
- numerical simulation /
- atomization /
- evaporation

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 网格无关性验证

Figure 2. Grid independence verification

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图 3 不同网格数量在3D截面处的温度分布

Figure 3. Temperature distribution of different mesh numbers at 3D section

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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 temperature and simulated temperature of different sections

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图 5 Box-Behnken组合设计法的实验点分布

Figure 5. Distribution of experimental points of Box-Behnken combined design method

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图 6 预测值-实际值、概率-预测值分布图

Figure 6. Distribution of residual error and predicted value，predicted value and actual value

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图 7 射流预冷参数对发动机进气温度的交互影响

Figure 7. Interaction of jet precooling parameters on engine inlet air temperature

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图 8 射流预冷参数对发动机进气温度的影响

Figure 8. Effect of parameters on engine inlet air temperature

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图 9 液滴运动轨迹图和各截面的温度云图

Figure 9. Droplet trajectory diagram and temperature cloud diagram of each section

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图 10 不同水气比下出口截面的温度畸变分析图

Figure 10. Temperature distortion analysis of outlet section under different water gas ratio

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图 11 不同水气比下不同截面平均温度对比图

Figure 11. Comparison diagram of average temperature of different sections under different water gas ratio

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图 12 不同液滴粒径下不同截面平均温度对比图

Figure 12. Comparison of average temperature of different sections under different droplet sizes

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表 1 设计因素编码与水平

Table 1. Code and level of design factors

因素	变量代号	水平值
因素	变量代号	−1	0	+1
水气比	X₁	0.02	0.05	0.08
液滴粒径	X₂	10	55	100
喷射速度	X₃	10	55	100
喷嘴锥角	X₄	15	45	75

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表 2 响应面试验设计和结果

Table 2. Response surface test design and results

试验号	水气比	液滴粒径/μm	喷射速度/（m/s）	喷嘴锥角/（°）
1	0.02	10	55	45
2	0.08	10	55	45
3	0.02	100	55	45
4	0.08	100	55	45
5	0.05	55	10	15
6	0.05	55	100	15
7	0.05	55	10	75
8	0.05	55	100	75
9	0.02	55	55	15
10	0.08	55	55	15
11	0.02	55	55	75
12	0.08	55	55	75
13	0.05	10	10	45
14	0.05	100	10	45
15	0.05	10	100	45
16	0.05	100	100	45
17	0.02	55	10	45
18	0.08	55	10	45
19	0.02	55	100	45
20	0.08	55	100	45
21	0.05	10	55	15
22	0.05	100	55	15
23	0.05	10	55	75
24	0.05	100	55	75
25	0.05	55	55	45
26	0.05	55	55	45
27	0.05	55	55	45
28	0.05	55	55	45
29	0.05	55	55	45

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表 3 回归方程的方差分析表

Table 3. Variance analysis of regression equation

来源	平方和	均方误差	F值	P值	备注
模型	35601.00	2542.93	270.52	< 0.0001	模型显著
X₁	21727.66	21727.66	2311.40	< 0.0001
X₂	9855.06	9855.06	1048.38	< 0.0001
X₃	1412.57	1412.57	150.27	< 0.0001
X₄	308.26	308.26	32.79	< 0.0001
X₁X₂	732.44	732.44	77.92	< 0.0001
X₁X₃	163.34	163.34	17.38	0.0009
X₂X₃	457.71	457.71	48.69	< 0.0001
X₂X₄	52.02	52.02	5.53	0.0338
X₃X₄	100.59	100.59	10.70	0.0056
X₁²	741.86	741.86	78.92	< 0.0001
X₃²	64.04	64.04	6.81	0.0206
残差	131.60	9.40
失拟项	131.60	13.16
纯误差	0	0

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表 4 回归方程误差统计分析

Table 4. Statistical analysis of regression equation error

统计项目	数值
标准偏差	3.07
变异系数	0.5771
精密度	64.5877
多元相关系数	0.9963
调整后的多元相关系数	0.9926
预测的多元相关系数	0.9788

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