补燃循环发动机推力室声阻尼特性分析及优化

孟敬芫; 李斌; 汪广旭; 肖虹; 杨宝娥

doi:10.13224/j.cnki.jasp.20230010

补燃循环发动机推力室声阻尼特性分析及优化

doi: 10.13224/j.cnki.jasp.20230010

1.
中国航天科技集团有限公司西安航天动力研究所液体火箭发动机技术重点实验室，西安 710100
2.
中国航天科技集团有限公司航天推进技术研究院，西安 710100

基金项目: 重点实验室基金（6142704210102）

详细信息

作者简介:
孟敬芫（1999-），男，硕士生，主要从事高频燃烧不稳定研究

中图分类号: V434.24
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- 文章访问数: 376
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- 被引次数: 0
出版历程
- 收稿日期: 2023-01-05
- 网络出版日期: 2024-06-14

Analysis and optimization of acoustic damping characteristics of staged combustion cycle engine thrust chamber

1.
Science and Technology on Liquid Rocket Engine Laboratory，Xi’an Aerospace Propulsion Institute，China Aerospace Science and Technology Corporation，Xi’an 710100，China
2.
Academy of Aerospace Propulsion Technology，China Aerospace Science and Technology Corporation，Xi’an 710100，China

摘要

摘要:
针对补燃循环液体火箭发动机的研制需求，开展推力室混合头部声阻尼特性研究及优化分析。建立考虑阻尼源项及整流栅声阻抗的三维线性声阻尼特性模型量化混合头部的阻尼耗散，通过求解Helmholtz方程获得推力室声模态频率及增长率，并对整流栅和喷嘴等阻尼部件进行优化。研究表明：流栅阻抗与喷嘴平均流均能产生阻尼效应，且平均流作用更为显著；整流栅小孔尺寸及间距、整流腔高度、喷嘴长度是提高混合头部阻尼效应的关键参数。
- 补燃循环液体火箭发动机 /
- 高频燃烧不稳定 /
- 混合头部 /
- 声阻尼优化 /
- 模态增长率
Abstract:
In view of the development requirements of the staged combustion cycle liquid rocket engine, a research and optimization analysis of the acoustic damping characteristics of the mixed head in the thrust chamber was carried out. A three-dimensional linear acoustic damping characteristic model considering the acoustic impedance of the flow distributor and the damping source term was established to quantify the damping dissipation of the mixed head. The acoustic mode frequency and growth rate of the thrust chamber were obtained by solving the Helmholtz equation, and the damping components such as the flow distributor and the injector were optimized. The results showed that the impedance of the flow distributor and the advective mean flow energy of the injector had a damping effect, and the average mean effect was more significant. The size and spacing of the hole within the flow distributor, the height of the oxidizer plenum and the length of the injector constituted the key parameters to improve the damping effect of the mixed head.
- staged combustion cycle liquid rocket engine /
- high frequency combustion instability /
- mixed head /
- acoustic damping optimization /
- mode growth rate

HTML

图 1 RD-170发动机混合头部^[20]

Figure 1. Mixed head of RD-170 engine^[20]

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图 2 整流栅结构平面视图^[20]

Figure 2. Plan view of flow distributor structure^[20]

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图 3 整流栅简化的多孔板模型

Figure 3. Simplified porous plate model of flow distributor

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图 4 $ \xi $和$ \delta $随频率的变化

Figure 4. Change of $ \xi $ and $ \delta $ with frequency

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图 5 整流栅等效阻抗幅频及相频特性

Figure 5. Amplitude frequency and phase frequency characteristics of equivalent impedance of flow distributor

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图 6 整流栅等效阻抗随R的变化

Figure 6. Change of equivalent impedance of flow distributor with R

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图 7 整流栅等效阻抗随d的变化

Figure 7. Change of equivalent impedance of flow distributor with d

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图 8 整流栅等效阻抗随u_c的变化

Figure 8. Change of equivalent impedance of flow distributor with u_c

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图 9 简化燃烧室几何模型

Figure 9. Geometric model of simplified combustion chamber

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图 10 简化燃烧室有限元模型

Figure 10. Finite element model of simplified combustion chamber

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图 11 1L模态频率随n的变化

Figure 11. Change of 1L mode frequency with n

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图 12 1T模态频率随n的变化

Figure 12. Change of 1T mode frequency with n

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图 13 2T模态频率随n的变化

Figure 13. Change of 2T mode frequency with n

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图 14 2T模态振型

Figure 14. Mode shape of 2T

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图 15 1L模态增长率随整流栅R和d的变化曲面

Figure 15. Surface of 1L mode growth rate varying with R and d of flow distributor

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图 16 1T模态增长率随整流栅R和d的变化曲面

Figure 16. Surface of 1T mode growth rate varying with R and d of flow distributor

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图 17 2T模态增长率随整流栅R和d的变化曲面

Figure 17. Surface of 2T mode growth rate varying with R and d of flow distributor

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图 18 1T模态增长率随整流腔高度变化

Figure 18. Change of 1T mode growth rate with flow distributor height

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图 19 1T模态频率随喷嘴长度的变化

Figure 19. Change of 1T mode frequency with injector length

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图 20 1T模态增长率随喷嘴长度的变化

Figure 20. Change of 1T mode growth rate with injector length

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图 21 第1个极值点对应的1T模态振型

Figure 21. 1T mode shape corresponding to the first extreme point

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图 22 第2个极值点对应的1T模态振型

Figure 22. 1T mode shape corresponding to the second extreme point

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$ c $	声速	$ \lambda $	波长
$ k $	波数	$ \omega $	模态频率
$ \rho $	密度	$ \varOmega $	复频率
t	时间	$ {D} $	偶极子源
$ {{\boldsymbol{n}}} $	燃烧室内壁单位法向量	$ {F} $	相间动量变化率
$ p $	压力	$ {{M}} $	单极子源
$ {{\boldsymbol{u}}} $	气相速度向量	$ {{P}} $	燃烧热释放变化率
$ {{{\boldsymbol{u}}}_{\text{c}}} $	液相速度向量	$ \dot Q $	气相燃烧热释放率
u_c	流速	$ {w_{\text{c}}} $	单位体积内液相到气相的质量转化率
$ Z $	声阻抗	$ {e_0} $	内能
$ \gamma $	比热比	$ {e_{{\text{c0}}}} $	液相的内能
$ \alpha $	增长率	Z	声阻抗
$ \theta $	声波入射角

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表 1 燃烧室尺寸参数

Table 1. Size parameters of combustion chamber mm

参数	数值
集气腔高度h	100
整流栅孔半径R	3.5
整流栅孔间距d	12
喷嘴孔径r	5.2
喷嘴长度L	150

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表 2 计算条件参数

Table 2. Calculation condition parameters

参数	数值
集气腔声速c₁/（m/s）	466.1
集气腔密度$ {\rho }_{1} $/（kg/m³）	165.3
喷嘴声速c₂/（m/s）	466.1
喷嘴密度$ {\rho }_{2} $/（kg/m³）	153
主燃烧室声速c₃/（m/s）	1249.7
主燃烧室密度$ {\rho }_{3} $/（kg/m³）	18.16
喷嘴流速u₂/（m/s）	200
整流栅孔内流速u_c/（m/s）	120

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表 3 不同最大单元的网格数量和模态频率

Table 3. Number of grids and mode frequencies of different maximum elements

最大单元/mm	网格数量	模态频率/Hz
最大单元/mm	网格数量	1L	1T	2T
70	80366	1249.4	1693	27449
50	87354	1249.4	1693	27449
30	134904	1249.4	1693	2748.8

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表 4 不同最小单元的网格数量和模态频率

Table 4. Number of grids and mode frequencies of different minimum elements

最小单元/mm	网格数量	模态频率/Hz
最小单元/mm	网格数量	1L	1T	2T
9	34048	1249.4	1693	2749
7	56027	1249.4	1693	2749
5	87354	1249.4	1693	2749
3	211030	1249.4	1693	2748.9

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表 5 公式估计值与仿真结果对比

Table 5. Comparison between formula estimation and simulation results

模态	模态频率
模态	理论值/Hz	仿真值/Hz	误差/%
1L	1086.7	1249.4	13
1T	1618.75	1693	4.39
2T	2685.58	2749	2.3

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表 6 喷嘴位置对模态频率的影响

Table 6. Influence of injector location on mode frequency

喷嘴位置	模态频率/Hz
喷嘴位置	1L	1T	2T
内层	1249.3	1694	2746.5
中层	1254.6	1696.9	2738.8
外层	1253.5	1700.2	2740.7

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表 7 不同阻尼项对1T模态频率及增长率影响

Table 7. Influence of adding different damping caps on 1T mode frequency and growth rate

阻尼项	模态频率/Hz	增长率
整流栅阻抗	1603.5	−2.8238
平均流源项	1594	−7.463
阻抗及源项	1593.1	−10.494
无阻尼项	1604	0

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