高马赫数空腔非定常流动机理

张培红; 程晓辉; 陈洪杨; 贾洪印; 罗磊; 唐银

doi:10.13700/j.bh.1001-5965.2021.0609

高马赫数空腔非定常流动机理

doi: 10.13700/j.bh.1001-5965.2021.0609

1.
中国空气动力研究与发展中心计算空气动力研究所，绵阳 621000
2.
航天时代飞鸿技术有限公司，北京 100094

基金项目: 国家数值风洞工程项目

详细信息

通讯作者:
E-mail：rorzey@buaa.edu.cn

中图分类号: V221⁺.3；O355
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出版历程
- 收稿日期: 2021-10-15
- 录用日期: 2022-01-17
- 网络出版日期: 2022-03-10
- 整期出版日期: 2023-08-31

Unsteady flow mechanism of high Mach number cavity

1.
Computational Aerodynamic Institute of China Aerodynamic Research & Development Center，Mianyang 621000，China
2.
Aerospace Times FeiHong Technology Company Limited，Beijing 100094，China

Funds: National Numerical Windtunnel Project

More Information

Corresponding author: E-mail：rorzey@buaa.edu.cnu.cn

摘要

摘要:
空腔流动广泛存在于飞行器中，内埋弹舱流动是最典型的空腔流动之一。空腔流动结构复杂，并且由于剪切层、涡和激波的相互作用，会产生强烈的压力脉动。针对高马赫数空腔强剪切、强激波的流动特点，提出基于非结构混合网格的中心型和迎风型格式混合方法，通过高马赫数空腔标模算例验证，计算得到空腔1阶、2阶主频与试验数据相比误差不超过5%，空腔噪声强度与试验数据相比误差不超过10 dB，验证了所提方法的可靠性。采用数值模拟方法，开展高马赫数（大于2）空腔流动的脉动特性研究，分析了不同马赫数对空腔声压级的影响，讨论不同马赫数下空腔脉动的产生的声学机制。研究表明：在高马赫数条件下，剪切层动力学与空腔声学的耦合减小，随马赫数增加，空腔振荡的物理机制由Rossiter模型的旋涡声学共振机制转变为闭箱声学机制。
- 空腔流动 /
- 脉动特性 /
- 声压等级 /
- 数值模拟 /
- 空腔噪声
Abstract:
The cavity flow widely exists in aircraft, and the flow in embedded weapon bay is one of the most typical cavity flows. The cavity flow has a complex structure and generates strong pressure fluctuations due to the interaction of shear layers, vortices, and shock waves. Using the unstructured hybrid mesh, a hybrid algorithm of central and upwind schemes is developed that focuses on the properties of high Mach number cavity flow. The cavity first-order and second-order dominant frequencies are calculated and verified by the numerical example of the high Mach number cavity standard model, with an error of no more than 5% compared with the experiment data. The cavity noise intensity has an error of no more than 10 dB compared with the experiment data, which verified the reliability of the method. The studies on the fluctuation characteristics of high Mach number (Ma> 2) cavity flow has been carried out with the numerical simulation method. The impact of various Mach numbers on the cavity's sound pressure level was examined, and it was also described how the cavity fluctuates acoustically at various Mach numbers. It is shown that the coupling between shear layer dynamics and cavity acoustics decreases at high Mach number conditions, and the physical mechanism of cavity oscillation changes from the vortex acoustic resonance mechanism of the Rossiter model to the closed-box acoustic mechanism as the Mach number increases.
- cavity flow /
- fluctuation characteristics /
- sound pressure level /
- numerical simulation /
- cavity noise

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图 1 空腔标模试验模型

Figure 1. Test model of cavity standard model

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图 2 空腔标模网格

Figure 2. Grid of cavity standard model

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图 3 空腔后壁面上监控点K的位置

Figure 3. Location of pressure orifice K on the rear wall of cavity

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图 4 监控点K处CFD计算得到的空腔声压等级与试验比较(Ma = 3.51)

Figure 4. Comparison of CFD calculation with test results of SPL for monitoring point K (Ma = 3.51)

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图 5 Ma = 2.0时，L/D = 8空腔不同时刻涡量云图和压力等值线图

Figure 5. Instantaneous vorticity contours and pressure contour plots at different times for L/D = 8 cavity at Ma = 2.0

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图 6 Ma = 3.0时，L/D = 8空腔不同时刻涡量云图和压力等值线图

Figure 6. Instantaneous vorticity contours and pressure contour plots at different times for L/D = 8 cavity at Ma = 3.0

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图 7 Ma = 4.0时，L/D = 8空腔不同时刻涡量云图和压力等值线图

Figure 7. Instantaneous vorticity contours and pressure contour plots at different times for L/D = 8 cavity at Ma = 4.0

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图 8 Ma =2.0, 3.0, 4.0时，L/D = 8空腔后壁面y/D = 0.75处监控点A的频谱图

Figure 8. Frequency specturum of monitoring point A at y/D = 0.75 for the rear wall of L/D = 8 cavity at Ma = 2.0, 3.0, 4.0

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图 9 CFD计算得到的斯特劳哈尔数同Rossiter声学模型和闭箱声学模型预测值比较

Figure 9. Comparison of Strouhal number of CFD calculation with predicted values of Rossiter’s equation and closed-box acoustic model

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表 1 CFD计算得到的监控点K不同模态频率、幅值与试验值比较

Table 1. Comparison of different frequencies and amplitudes of CFD calculation with text results for monitoring point K

模态	SPL频率/Hz		SPL幅值/dB		频率误差/%	幅值误差/%
模态	试验值	计算值	试验值	计算值	频率误差/%	幅值误差/%
1阶模态	287	275	132.5	135.6	4.18	3.1
2阶模态	695	689	132.1	135.8	0.86	3.7
3阶模态	1152	1195	132.8	138	3.73	5.2
4阶模态	1527	1516	131	134.7	0.72	3.7

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表 2 CFD计算得到的全局声压等级与试验值比较

Table 2. Comparison CFD calculation with text results of OASPL

数据类型	试验值/dB	计算值/dB	误差/dB
OASPL	151.94	154.79	2.85

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表 3 CFD计算、Rossiter声学模型和闭箱声学模型得到的$ fL/{U_\infty } $

Table 3. Strouhal Number of CFD calculation with predicted values of Rossiter’s equation and closed-box acoustic model

Ma	1阶模态			2阶模态			3阶模态			4阶模态
Ma	CFD 计算值	Rossiter 声学模型	闭箱声学模型	CFD 计算值	Rossiter 声学模型	闭箱声学模型	CFD 计算值	Rossiter 声学模型	闭箱声学模型	CFD 计算值	Rossiter 声学模型	闭箱声学模型
0.85	0.211 76	0.294 24	0.629 31	0.677 84	0.686 57	1.258 61	1.099 90	1.078 89	1.887 91	1.465 66	1.471 21	2.517 21
1.35	0.267 60	0.257 72	0.432 64	0.628 80	0.601 36	0.865 27	0.955 50	0.944 99	1.297 91	1.266 66	1.288 62	1.730 55
2.0	0.254 48	0.231 12	0.335 41	0.559 85	0.539 27	0.670 82	0.839 77	0.847 43	1.006 23	1.170 59	1.155 59	1.341 64
3.0	0.191 76	0.211 43	0.278 89	0.557 84	0.493 34	0.557 77	0.836 76	0.775 25	0.836 66	1.192 52	1.057 16	1.115 55
4.0	0.241 26	0.202 36	0.256 17	0.562 93	0.472 18	0.512 35		0.742 33	0.768 52	1.025 99	1.011 82	1.024 70

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