考虑燃气腔影响的燃烧室声学模态特性数值仿真

张泽昊; 董立宝; 赵粒优; 郭康康; 庞建国

doi:10.13224/j.cnki.jasp.20250119

考虑燃气腔影响的燃烧室声学模态特性数值仿真

doi: 10.13224/j.cnki.jasp.20250119

1.
太原卫星发射中心，太原 030031
2.
中国运载火箭技术研究院首都航天机械有限公司，北京 100076
3.
航天工程大学宇航科学与技术系，北京 101416

基金项目: 国家自然科学基金面上项目（51876219）

详细信息

作者简介:
张泽昊（1997-），男，工程师，硕士，主要从事液体火箭发动机燃烧不稳定性方面的研究。E-mail：864424640@qq.com

通讯作者:
庞建国（1970-），男，研究员级高级工程师，硕士，主要从事航天测试与发射方面的研究。E-mail：lili19720605@163.com

中图分类号: V434.1
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- 被引次数: 0
出版历程
- 收稿日期: 2025-03-10
- 网络出版日期: 2025-06-28

Numerical simulation of acoustic mode characteristics of combustion chamber considering influence of dome

1.
Taiyuan Satellite Launch Centre，Taiyuan 030031，China
2.
Capital Aerospace Machinery Limited，China Academy of Launch Vehicle Technology，Beijing 100076，China
3.
Department of Aerospace Science and Technology，Space Engineering University，Beijing 101416，China

摘要

摘要:
基于计算气动声学/低阶热声网络耦合方法开展了含燃气腔燃烧室声学模态特性数值仿真，计算获得了燃烧室主要声学模态的特征频率、阻尼率及声压分布云图，验证了该耦合算法精度与效率，并对比分析了燃气腔对声学模态特性的影响。结果表明：考虑燃气腔影响后，燃气腔会与燃烧室声压分布相互耦合，导致燃烧室1阶横向、纵向模态阻尼率下降24.5%、16%，但对其特征频率影响不明显；另外，相比于常规计算气动声学法，耦合方法在保证计算精度的条件下，使计算效率提升49%，非常适合在工程中对多喷注器液体火箭发动机燃烧室开展声学特性研究。
- 燃气腔 /
- 燃烧室 /
- 声学模态特性 /
- 计算气动声学 /
- 低阶热声网络
Abstract:
Numerical simulation of the acoustic mode characteristics of the combustion chamber with the dome was carried out based on the coupled computational aeroacoustic (CAA)/low-order thermoacoustic network method. The eigenfrequencies, damping rates and acoustic pressure distribution clouds of the main acoustic modes of the combustion chamber were obtained, the accuracy and efficiency of the coupling methods were verified, and the influence of the dome on the acoustic mode characteristics was compared and analyzed. The results showed that, after considering the influence of the dome which was coupled with the acoustic pressure distribution of the combustion chamber, the damping rate of the first-order transverse and longitudinal modes of the combustion chamber was reduced by 24.5% and 16%, but the effect on eigenfrequency was not obvious; compared with the CAA method, the coupling method can improve the calculation efficiency by 49% under the condition of ensuring the calculation accuracy, making it very suitable for the engineering of multi-nozzle liquid rocket engine combustion chamber.
- dome /
- combustion chamber /
- acoustic mode characteristics /
- computational aero acoustic /
- low-order thermoacoustic network

HTML

图 1 计算气动声学与低阶热声网络耦合方法示意图^[18]

Figure 1. Schematic diagram of the CAA/low-order thermoacoustic network coupling method^[18]

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图 2 燃烧室几何结构（单位：mm）

Figure 2. Configuration of the combustion chamber （unit：mm）

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图 3 燃烧室平均流场云图

Figure 3. Mean flow field variable distribution of the combustion chamber

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图 4 喷注器单元低阶热声网络模型示意图

Figure 4. Schematic diagram of the low-order thermoacoustic model of the injector element

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图 5 燃烧室边界条件及计算域示意图

Figure 5. Schematic diagram of boundary conditions and computational domain for combustion chamber mesh

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图 6 燃烧室1阶切向模态声压分布云图

Figure 6. Sound pressure distribution contour at 1T mode of the combustion chamber

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图 7 九喷注器发动机示意图^[16]

Figure 7. Schematic diagram of the nine-injector rectangular engine^[16]

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图 8 九喷注器发动机几何结构（单位：mm）

Figure 8. Specific geometry of the nine-injector rectangular engine （unit：mm）

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图 9 九喷注器发动机平均流场分布

Figure 9. Mean flow field variable distribution of the nine-injector rectangular engine

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图 10 不同方法下燃烧室声学网格示意图

Figure 10. Schematic diagram of the acoustic mesh of the combustion chamber by different methods

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图 11 不同方法获得的燃烧室1W模态声压分布云图

Figure 11. Sound pressure distribution contours at 1W mode of the combustion chamber obtained by different methods

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图 12 不同方法获得的燃烧室1L模态声压分布云图

Figure 12. Sound pressure distribution contours at 1L mode of the combustion chamber obtained by different methods

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图 13 不同方法获得的燃烧室1W模态燃气腔处声压分布云图

Figure 13. Sound pressure distribution contours at 1W mode of the dome obtained by different methods

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图 14 不同方法获得的燃烧室1L模态燃气腔处声压分布云图

Figure 14. Sound pressure distribution contours at 1L mode of the dome obtained by different methods

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图 15 无燃气腔情况下燃烧室1W、1L模态声压分布云图

Figure 15. Sound pressure distribution contours at 1W and 1L modes of the combustion chamber without the dome

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表 1 燃烧室平均流场参数

Table 1. Mean flow field variables of the combustion chamber

参数	数值
密度/（kg/m³）	1.98
压力/kPa	165
马赫数	0.25
入口温度/K	290
声速/（m/s）	341
质量流量/（kg/s）	1.15

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表 2 燃烧室1阶切向模态的特征频率和阻尼率及与其他文献对比

Table 2. 1T mode eigenfrequency and damping rates of combustion chamber and comparison with others

参数	仿真（TM来自实验）^[18]	实验^[18,21]	本文	误差/%
参数	仿真（TM来自实验）^[18]	实验^[18,21]	本文	本文与仿真（TM来自实验）^[18]	本文与试验^[18,21]
特征频率/Hz	2158	2160	2133.50	−1.1	−1.2
阻尼率/（rad/s）	480	585	422.23	−12	−27.8

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表 3 燃气腔平均流场参数

Table 3. Parameter values for the mean flow field variables in the dome

参数	数值
压力/10⁶ Pa	1.36
温度/K	600
密度/（kg/m³）	8.33
平均流速/（m/s）	14.75

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表 4 边界条件

Table 4. Boundary conditions

边界位置	参数	数值及说明
氧化剂入口	质量流量/（kg/s）	0.08417
	温度/K	635
	物种组分	100%O₂
燃料入口	质量流量/（kg/s）	0.02369
	温度/K	287
	物种组分	100%CH₄
出口	压力/Pa	101325
壁面	无滑移壁面

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表 5 不同方法获得的燃烧室1W、1L模态特征频率及阻尼率

Table 5. 1W，1L mode eigenfrequency and damping rates of the combustion chamber obtained by different methods

数值仿真方法	特征频率/Hz		阻尼率/（rad/s）
数值仿真方法	1W	1L	1W	1L
计算气动声学	2529.5	3262.4	−103.0	921.7
耦合方法	2533.6	3316.1	−116.6	1152.7

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表 6 两种方法消耗的资源对比

Table 6. Comparison of the resources consumed by different methods of numerical simulation

数值仿真方法	网格数	求解自由度数	仿真时间
计算气动声学	185530	921224	19 min
耦合方法	81337	398110	9 min42 s

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表 7 不同情况下燃烧室1W、1L模态的特征频率及阻尼率

Table 7. 1W，1L mode eigenfrequency and damping rates of the combustion chamber under different configurations

工况	特征频率/Hz		阻尼率/（rad/s）
工况	1W	1L	1W	1L
含燃气腔	2533.6	3316.1	−116.6	1152.7
无燃气腔	2522.3	3175.5	−93.62	1379.16

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