过渡型凹腔超声速燃烧流动振荡抑制方法

蔡建华; 田野; 肖保国; 邢建文

doi:10.13224/j.cnki.jasp.20210495

过渡型凹腔超声速燃烧流动振荡抑制方法

doi: 10.13224/j.cnki.jasp.20210495

中国空气动力研究与发展中心空天技术研究所，四川绵阳 621000

基金项目: 中国空气动力研究与发展中心基础和前沿技术研究基金（PJD20190073）

详细信息

作者简介:
蔡建华（1993-），男，助理研究员，硕士，主要从事超声速燃烧流动研究。E-mail：caijianhua.1993@163.com

通讯作者:
肖保国（1980-），男，研究员，博士，主要从事超声速燃烧流动研究。E-mail：xbgxl@163.com

中图分类号: V235.21
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出版历程
- 收稿日期: 2021-09-06
- 网络出版日期: 2022-10-26

Suppressing oscillation method of supersonic combustion and flow in transitional cavity

Aerospace Technology Institute,China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China

摘要

摘要:
针对长深比为10.0的过渡型凹腔在隔离段入口马赫数为3.0条件下存在的冷流自激振荡现象，提出了一种凹腔内增加肋条抑制振荡的方案。通过试验和数值计算，对该方案抑制振荡的效果进行了检验，并分析了肋条增加前后燃烧室流场结构和燃烧性能的差别。研究发现：通过在凹腔内增加肋条能够消除过渡型凹腔冷流工况下存在的175.8 Hz的自激振荡，燃烧流场也更加稳定；增加肋条后凹腔的稳焰能力有所降低，部分在凹腔未完全燃烧的煤油进入扩张段后继续发生反应，从而使燃烧区向下游延伸、增大，发动机的燃烧效率和净推力分别降低5.4%和8.9%，但推力更加平稳；燃烧室一维平均热流密度峰值由2.9 MW/m²降低至1.8 MW/m²，燃烧室的热环境大幅改善。
- 过渡型凹腔 /
- 超声速燃烧流动 /
- 抑制振荡 /
- 声压级 /
- 燃烧性能
Abstract:
Targeting the phenomenon of non-reacting flow self-excited oscillation in a traditional cavity with a length-to-depth of 10.0 under the isolator entrance condition of Mach number 3.0, a scheme to suppress the oscillation by adding a rib in the cavity was proposed. Through experiments and numerical calculations, the effect of this scheme on suppressing oscillation was verified, and the differences in the flow field structure and combustion performance of the combustor with/without the rib were analyzed. It was found that adding a rib in the cavity can effectively eliminate the self-excited oscillation of 175.8 Hz under the non-reacting flow condition, and the reacting flow field was more stable. The flame stabilization ability of the cavity was reduced after the rib was added, and some kerosene not completely burned in the cavity continued to react after entering the divergent section, so as to extend and enlarge the combustion zone downstream. The combustion efficiency and net thrust of the engine were reduced by 5.4% and 8.9%, respectively, but the thrust was more stable. The peak value of one-dimensional averaged heat flux was also reduced from 2.9 MW/m² to 1.8 MW/m², which optimized the thermal environment of the combustor.
- transitional cavity /
- supersonic combustion and flow /
- suppressing oscillation /
- sound pressure level (SPL) /
- combustion performance

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图 1 直连式脉冲燃烧风洞^[10]

Figure 1. Direct-connected pulse combustion wind tunnel^[10]

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图 2 风洞试验段（单位：mm）

Figure 2. Test section of wind tunnel （unit：mm）

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图 3 喷注支杆示意图（单位：mm）

Figure 3. Sketch map of the injection strut （unit：mm）

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图 4 两种不同构型的凹腔

Figure 4. Two cavities with different configurations

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图 5 基础凹腔计算模型

Figure 5. Calculation model of basic cavity

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图 6 网格无关性验证

Figure 6. Grid independence verification

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图 7 基础凹腔一个周期内波系结构

Figure 7. Waves system of basic cavity in one period

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图 8 冷流工况下基础凹腔的壁面压力

Figure 8. Wall pressure of basic cavity under non-reacting flow

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图 9 基础凹腔流场不同切面马赫数分布

Figure 9. Mach number distributions on different slices of basic cavity

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图 10 基础凹腔对称面流场结构

Figure 10. Flow field on symmetry plane of basic cavity

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图 11 三维凹腔波系结构

Figure 11. Waves system of three-dimensional cavity

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图 12 冷流流动时声压级曲线

Figure 12. Sound pressure level of non-reacting flow

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图 13 三维凹腔不同切面流场结构

Figure 13. Flow field at different slices of three-dimensional cavity

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图 14 两种凹腔燃烧流场对比

Figure 14. Comparison of reacting flow fields of two cavities

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图 15 燃烧工况下基础凹腔壁面压力

Figure 15. Wall pressure of basic cavity under reacting flow

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图 16 燃烧工况下三维凹腔壁面压力

Figure 16. Wall pressure of three-dimensional cavity underreacting flow

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图 17 燃烧工况下基础凹腔内非稳态现象

Figure 17. Unsteady phenomenon of basic cavity under reacting flow

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图 18 燃烧工况下三维凹腔内的马赫数和温度分布

Figure 18. Mach number and temperature distribution of three-dimensional cavity under reacting flow

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图 19 燃烧工况下的声压级曲线

Figure 19. Sound pressure level under reaction flow

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图 20 燃烧工况下凹腔中心线沿程压力分布对比

Figure 20. Comparison of wall pressure distributions along centerline under reacting flow

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图 21 壁面热流密度分布对比

Figure 21. Comparison of heat flux distributions

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图 22 壁面一维热流密度分布对比

Figure 22. Comparison of one-dimensional heat flux distributions

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表 1 来流条件

Table 1. Inflow condition

马赫数	分子量	摩尔分数/%			静温/K	静压/kPa
马赫数	分子量	水	氧气	氮气	静温/K	静压/kPa
3.0	26.71	21.4	21.3	57.3	545.2	44.0

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表 2 燃烧性能

Table 2. Combustion performance

参数		基础凹腔	三维凹腔
燃烧效率/%	凹腔出口处	76.6	48.1
燃烧效率/%	扩张段出口处	98.5	93.1
壁面压力积分/N	冷流工况	175.5*（38.2～312.9）	178.8
壁面压力积分/N	燃烧工况	−109.5*（−142.8～−76.2）	−80.7
净推力/N		285.0*	259.5
注：右上角带有星号“*”角标的数字表示推力积分波动值的平均值。

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