航天推进技术研究院主办
[1]尚冬琴,张峥岳,严 宇,等.热吹风条件下带声腔燃烧室阻尼特性研究[J].火箭推进,2018,44(04):60-67.
s.Study on damping characteristic of combustion chamber with acoustic resonators under hot blowing condition[J].Journal of Rocket Propulsion,2018,44(04):60-67.
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s.Study on damping characteristic of combustion chamber with acoustic resonators under hot blowing condition[J].Journal of Rocket Propulsion,2018,44(04):60-67.
热吹风条件下带声腔燃烧室阻尼特性研究
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
44
期数:
2018年04期
页码:
60-67
栏目:
测控与试验
出版日期:
2018-08-31
- Title:
- Study on damping characteristic of combustion chamber with acoustic resonators under hot blowing condition
- 文章编号:
- 1672-9374(2018)04-0060-08
- 分类号:
- V430-34
- 文献标志码:
- A
- 摘要:
- 为了获得热吹风条件下某带声腔燃烧室的阻尼特性,研究了声腔、流动介质、温度及激励源位置等因素对声波传递及衰减的影响,并对比了冷态(无流动)条件下模拟燃烧室的实验和计算压力-时间曲线。结果表明:声腔的加入,使燃烧室的声学振型发生了频移,相应振型幅值减小; 冷态(无流动)条件下激发的振型更多,冷态(无流动)条件下与热吹风条件下测得的声腔加入对1L和1T振型的影响规律一致,冷态(无流动)条件下模拟燃烧室压力-时间曲线的实验结果和计算结果趋势一致。验证了数值计算模型的正确性和冷态声学模拟可作为研究燃烧室声振荡的有效手段。
- Abstract:
- In order to obtain damping properties of a combustor with acoustic resonators under hot blowing condition, influence of resonator, flowing medium, temperature and stimulation source location on sonic wave propagation and attenuation are investigated. Experimental and calculated pressure-time curves of modular combustor under static cold state condition are compared. The results show that resonators can make the acoustics vibration frequency of the combustor shift and result in lower oscillation amplitude; more vibration modes can be stimulated under the static cold condition; the influence rules of the acoustic resonator on 1L and 1T oscillation modes under static cold and hot blowing conditions are almost the same. The correctness of numerical calculation model and a fact that the sonic simulation in cold static flow can be used as effective means to investigate the sonic oscillation properties of combustor are verified.
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Hu Wei,Li Ping.The acoustic cavity technique options and test validation of the bipropellant orbit control rocket engine[J].Journal of Rocket Propulsion,2006,32(04):7.
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备注/Memo
收稿日期:2018-05-02
基金项目: 有声腔燃烧室燃烧高频不稳定性的设计规范和实验研究(613193020202)
作者简介: 尚冬琴(1986—),女,硕士,研究领域为液体火箭发动机喷雾燃烧技术
更新日期/Last Update:
1900-01-01