自燃推进剂模型燃烧室高频纵向燃烧不稳定性

汪广旭; 谭永华; 庄逢辰

doi:10.13224/j.cnki.jasp.2020.08.002

自燃推进剂模型燃烧室高频纵向燃烧不稳定性

doi: 10.13224/j.cnki.jasp.2020.08.002

基金项目: 装备预研重点实验室基金（6142704190101）

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出版历程
- 收稿日期: 2020-01-09
- 刊出日期: 2020-08-28

High frequency longitudinal combustion instability of modeled hypergolic propellants combustor,

1.
National Key Laboratory of Science and Technology on Liquid Rocket Engines,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
3.
Department of Aerospace Science and Technology,Space Engineering University,Beijing 101416,China

摘要

摘要: 采用集总燃烧模型对某自燃推进剂模型燃烧室的高频纵向燃烧不稳定性进行了分析,计算了液滴蒸发速率沿轴向分布,忽略化学反应时间,近似采用蒸发速率峰值位置代替集中燃烧锋面位置,采用NASA经验公式给出了相应的敏感时滞和相互作用指数,建立了考虑自燃推进剂液滴蒸发过程的高频纵向燃烧不稳定性量化分析模型。基于系统振荡增益变化曲线,分析了不同液滴初始速度条件下稳定性趋势。研究表明:集中燃烧锋面位置对于高频纵向燃烧振荡具有重要影响,液滴平均粒径和液滴初始速度的增加都会导致其向下游移动,相应振荡增益会减小,稳定性提高。当平均粒径超过150 μm时,模型燃烧室振荡增益幅值降低至10以下,达到了理论上的稳定。
- 自燃推进剂 /
- 燃烧不稳定 /
- 集总燃烧模型 /
- 液滴蒸发 /
- 集中燃烧锋面
Abstract: High frequency longitudinal combustion instability of a modeled hypergolic propellants combustor was analyzed through concentrated combustion model, in which the distribution of droplet evaporation rate along flow axis was calculated. The peak position of evaporation rate was used as the position of concentrated combustion front when the chemical time was ignored and the empirical correlation of NASA was used to provide sensitive time and interaction index. Then the model for quantity analysis of high frequency longitudinal combustion instability was built considering the hypergolic propellants droplet evaporation. Based on the curves of system oscillation gain, stability tendency under different conditions of initial droplet radius and injection velocity was analyzed. It showed that the position of concentrated combustion front was critical to high frequency longitudinal combustion instability, improvement of averaged initial droplet radius and velocity could make the front far away from the injection face, and the corresponding oscillation gain could be reduced too, making the system more stable. Especially, when the averaged droplet radius got bigger than 150 μm, oscillation gain of the modeled combustor could be smaller than 10 and the combustor could become stable in theory.
- hypergolic propellants /
- combustion instability /
- concentrated combustion model /
- ,droplet evaporation /
- concentrated combustion front

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参考文献(21)

[1]	CROCCO L,CHENG S I.Theory of combustion instability in liquid propellant rocket motors［M］.London:Butter-Worths Publication Limited,1956.
[2]	HARRJE D T,REARDON F H.Liquid propellant rocket combustion instability［R］.NASA SP-194,1972.
[3]	聂万胜,丰松江.液体火箭发动机燃烧动力学模型与数值计算［M］.北京:国防工业出版社,2011.
[4]	MATTHEW J C.Extensions to the time lag models for practical application to rocket engine stability design［D］.Harrisburg,US:The Pennsylvania State University,2010.
[5]	汪广旭,郭灿琳,石晓波,等.基于时滞模型的纵向燃烧不稳定性分析［J］.推进技术,2016,37(6):1129-1135. WANG Guangxu,GUO Canlin,SHI Xiaobo,et al.Analysis of longitudinal combustion instability based on time lag model［J］.Journal of Propulsion Technology,2016,37(6):1129-1135.(in Chinese)
[6]	MUSS J A,NGUYEN T V,JOHNSON C W.User’s manual for rocket combustor interactive design (ROCCID) and analysis computer program volume:Ⅰ［R］.NASA CR 187109,1990.
[7]	MUSS J A,NGUYEN T V,JOHNSON C W.User’s manual for rocket combustor interactive design (ROCCID) and analysis computer program volume Ⅱ［R］.NASA CR 187110,1990.
[8]	DOWLING A P,STOW S R.Acoustic analysis of gas turbine combustors［J］.Journal of Propulsion and Power,2003,19 (5):751-764.
[9]	FORTUNATO B,CAMPOREALE S M,CAMPA G.A finite element method for three-dimensional analysis of thermoacoustic combustion instability［J］.Journal of Engineering for Gas Turbine and Power,2011,23(1):101-114.
[10]	YU Y C,SISCO J C.Effects of mean flow entropy waves and boundary conditions on longitudinal combustion instability［J］.Combustion Science and Technology,2010,182(7):739-776.
[11]	TAMANAMPUDI G M R,ANDERSON W E.Development of combustion instability analysis tool by incorporating combustion response models［R］.AIAA 2015-4165,2015.
[12]	尹婷,聂万胜,何浩波.偏二甲肼液滴燃烧特性及影响因素实验研究［J］.火箭推进,2014,40(5):29-36. YIN Ting,NIE Wansheng,HE Haobo.Experimental study on combustion characteristics of UDMH droplet and influence factors on combustion［J］.Journal of Rocket Propulsion,2014,40(5):29-36.(in Chinese)
[13]	夏益志,杨伟东,王勇,等.燃烧条件下自燃推进剂的雾场及火焰实验研究［J］.火箭推进,2019,45(4):26-31. XIA Yizhi,YANG Weidong,WANG Yong,et al.Experimental study on the spray and flame of hypergolic bipropellants in hot-fire test［J］.Journal of Rocket Propulsion,2019,45(4):26-31.(in Chinese)
[14]	张蒙正,徐胜利.超临界环境下煤油和UDMH单滴燃烧现象［J］.火箭推进,2013,39(5):1-6. ZHANG Mengzheng,XU Shengli.Combustion phenomena of kerosene and UDMH droplets in supercritical environment［J］.Journal of Rocket Propulsion,2013,39(5):1-6.(in Chinese)
[15]	庄逢辰.液体火箭发动机喷雾燃烧的理论、模型与应用［M］.长沙:国防科技大学出版社,1995.
[16]	陈新华,吴冲华,佟连捷.大气中N2O4/UDMH推进剂蒸发特性的研究［J］.推进技术,2000,21(2):77-80. CHEN Xinhua,WU Chonghua,TONG Lianjie.Evaporation characteristic of N2O4/UDMH propellant in the air［J］.Journal of Propulsion Technology,2000,21(2):77-80.(in Chinese)
[17]	WILLIAM A S.Two-time-variable perturbation theory for liquid rocket combustion instability［J］.Journal of Propulsion and Power,2016,32(3):755-776.
[18]	聂万胜,庄逢辰.自燃推进剂火箭发动机燃烧不稳定性研究［J］.推进技术,2000,21(4):63-76. NIE Wansheng,ZHUANG Fengchen.Hypergolic propellant rocket engine combustion instability studies［J］.Journal of Propulsion Technology,2000,21(4):63-76.(in Chinese)
[19]	聂万胜,庄逢辰.自燃推进剂火箭发动机稳态燃烧过程的数值模拟［J］.推进技术,1998,19(5):6-9. NIE Wansheng,ZHUANG Fengchen.Numerical simulation of stable combustion process in earth storable bipropellant rocket engine［J］.Journal of Propulsion Technology,1998,19(5):6-9.(in Chinese)
[20]	赵红玲,王凤坤,陈圣坤.气液物性手册［M］.北京:化学工业出版社,2006.
[21]	洪鑫,程惠尔.液体火箭发动机燃烧室波动过程数值分析［J］.推进技术,1999,20(2):656-660.