基于DMD的双喉道矢量喷管的流场重构与分析

王建明; 刘晓东; 夏瑄泽; 王成军

doi:10.13224/j.cnki.jasp.20210679

基于DMD的双喉道矢量喷管的流场重构与分析

doi: 10.13224/j.cnki.jasp.20210679

沈阳航空航天大学航空发动机学院辽宁省航空推进系统先进测试技术重点实验室，沈阳 110136

基金项目: 国家自然科学基金（51476106）

详细信息

作者简介:
王建明（1975-），男，副教授，博士。研究领域为流体机械、空气动力学。 Email：jmwang75@163.com

中图分类号: V231.1
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- 被引次数: 0
出版历程
- 收稿日期: 2021-11-29
- 网络出版日期: 2024-01-20

Flow field reconstruction and characteristic analysis of dual-throat control vector nozzle based on dynamic mode decomposition

Liaoning Key Laboratory of Advanced Test Technology for Aeronautical Propulsion System，School of Aero-engine，Shenyang Aerospace University，Shenyang 110136，China

摘要

摘要:
采用分离涡模拟方法对双喉道矢量喷管的三维流场进行数值模拟，分析原始流场的压力系数以及密度梯度分布。运用动力学模态分解技术（DMD）对喷管z=0截面压力系数进行模态分解，选取得到的模态重构流场，将对应的模态进行时间演化并分析其特性。结果表明：利用动力学模态分解得到的前5阶模态可以较完整地重构出双喉道矢量喷管的压力系数场，其中第1模态主要反映的是分离激波的摆动现象以及其对回流区与主流之间剪切层的压力脉动的影响。2阶模态的主要特征是剪切层中的涡系脱落。3阶模态中主要反映的是分离激波强度的变化。4阶、5阶模态主要表现为分离激波位置以及强度上的高阶振荡。
- 推力矢量技术 /
- 双喉道矢量喷管 /
- 非定常流动 /
- 动力学模态分解 /
- 激波边界层干扰
Abstract:
The three-dimensional flow field of the thrust vectoring nozzle was simulated by detached eddy simulation method, and the pressure coefficient and density gradient distribution of flow field were analyzed. The dynamic modal decomposition (DMD) technology was applied to modal decomposition of the pressure coefficient of the z=0 section, the obtained modal recombination flow field was selected to evolve in time. The results indicated that the first five-order modes obtained by dynamic modal decomposition can be used to reconstruct the pressure coefficient field of the dual-throat control vector nozzle more completely. The first-order mode mainly illustrated the swing phenomenon of the separated shock wave and its influence on the pressure pulsation of the shear layer between the recirculation zone and the main flow; the second-order mode mainly illustrated the separation of the vortex system in the shear layer. The third-order mode mainly illustrated the change in the intensity of the separated shock wave, the fourth and fifth-order modes were mainly manifested as high-order oscillations in the position and intensity of the separated shock wave and the shear layer near the recirculation zone.
- thrust vector technology /
- dual throat vector nozzle /
- unsteady flow /
- dynamic mode decomposition /
- shock boundary layer interference

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图 1 喷管主要结构

Figure 1. Design parameters of the dual-injection

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图 2 喷管计算域与计网格

Figure 2. Nozzle calculation domain and grid

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图 3 网格无关性验证与实验^[9]的对比

Figure 3. Comparison of the experimental^[9] and computational pressure

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图 4 喷管内部流场压力系数分布

Figure 4. Pressure coefficient contour distribution of flow field in the nozzle interior

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图 5 z=0面马赫数等值线

Figure 5. Mach number contour at z=0

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图 6 z=0面脉动压力方均根分布

Figure 6. Root mean square distribution of pulsating pressure at z=0

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图 7 z=0面马赫数分布

Figure 7. Mach number distribution at z=0

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图 8 z=0面压力系数分布

Figure 8. Pressure coefficient contour distribution at z=0

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图 9 z=0面X方向密度梯度分布

Figure 9. X-direction density gradient distribution at z=0

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图 10 z=0面Y方向密度梯度分布

Figure 10. Y-direction density gradient distribution at z=0

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图 11 喷管DMD幅频图

Figure 11. Power spectrum of nozzle from DMD

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图 12 喷管零阶模态压力系数云图

Figure 12. Pressure coefficient contour distribution of the mean flow mode

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图 13 流场重构相对误差图

Figure 13. Relative error between reconstruction and actual flow field

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图 14 DMD重构流场压力系数分布

Figure 14. Pressure coefficient distribution of reconstructed flow field from DMD

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图 15 DMD1阶模态压力系数云图

Figure 15. Pressure coefficient contour of the frist DMD mode

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图 16 DMD2阶模态压力系数云图

Figure 16. Pressure coefficient contour of the second DMD mode

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图 17 DMD3阶模态压力系数云图

Figure 17. Pressure coefficient contour of the third DMD mode

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图 18 DMD4阶模态压力系数云图

Figure 18. Pressure coefficient contour of the fourth DMD mode

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图 19 DMD5阶模态压力系数云图

Figure 19. Pressure coefficient contour of the fifth DMD mode

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表 1 喷管主要设计参数

Table 1. Designed parameters of the nozzle

设计参数	数值
第1喉道高度h_dt1/mm	2967.736
第2喉道高度h_dt2/mm	2967.736
喷管宽度/mm	101.6
空腔长度l/mm	76.2
扩张角θ₁/（°）	10
收敛角θ₂/（°）	20
二次流入射角α/（°）	30

下载: 导出CSV

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