航天推进技术研究院主办
[1]张 锋,杨伟东,胡洪波,等.氧化亚氮/乙烯推进剂预混燃烧特性试验研究[J].火箭推进,2019,45(03):41-47.
ZHANG Feng,YANG Weidong,HU Hongbo,et al.Experimental investigation of premixed combustion characteristics of N2O/C2H4 propellants[J].Journal of Rocket Propulsion,2019,45(03):41-47.
点击复制
ZHANG Feng,YANG Weidong,HU Hongbo,et al.Experimental investigation of premixed combustion characteristics of N2O/C2H4 propellants[J].Journal of Rocket Propulsion,2019,45(03):41-47.
氧化亚氮/乙烯推进剂预混燃烧特性试验研究
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
45
期数:
2019年03期
页码:
41-47
栏目:
研究与设计
出版日期:
2019-06-30
- Title:
- Experimental investigation of premixed combustion characteristics of N2O/C2H4 propellants
- 文章编号:
- 1672-9374(2019)03-0041-07
- Keywords:
- nitrous-oxide-based composite mono-propellant; ethylence; porous material; premixed combustion; characteristic velocity; combustion efficiency
- 分类号:
- V312
- 文献标志码:
- A
- 摘要:
- 氧化亚氮基单元复合推进剂是一种新型、高能、无毒的单组元推进剂,具有广阔的应用前景。开展了氧化亚氮/乙烯推进剂在室压0.7 MPa和1.0 MPa条件下、混合比6.2～10.6范围内的预混燃烧特性试验,获得了混合比、燃烧室特征长度等对特征速度和燃烧效率的影响规律。试验结果表明:当量孔径为65 μm、厚度为5 mm的不锈钢多孔材料具有良好的防回火效果,所有试验工况均未发生燃烧室回火现象; N2O/C2H4推进剂的理论特征速度和试验特征速度均随着混合比的增大而减小,最高燃烧效率达到了95.0%; 随着燃烧室特征长度的不断增大,燃烧效率先增大后减小,对所试验的特定喷注器结构的铜热沉模型燃烧室来说,最佳的燃烧室特征长度在1.675 m左右。
- Abstract:
- Nitrous-oxide-based composite mono-propellant is a new, non-toxic, mono-propellant with high performance and broad application prospects.A series of premixed combustion tests with N2O/C2H4 propellants were carried out, covering the mixture ratio range of 6.2～10.6 at the chamber pressure of 0.7 MPa and 1.0 MPa.The effects of the mixture ratio and the combustion chamber characteristic length on the characteristic velocity and the combustion efficiency were obtained.The results showed that, the anti-flashback effect of stainless steel porous materials with the equivalent pore diameter of 65 μm and the thickness of 5 mm was so good that no flashback occurred in all combustion tests.The theoretical and measured characteristic velocity decreased with the increase of the mixture ratio.The maximum combustion efficiency was 95.0%.As the combustion chamber characteristic length increased, the combustion efficiency increased first and then decreased.For the model combustion chamber studied in this paper, the best combustion chamber characteristic length was about 1.675m.
参考文献/References:
[1] VOZOFF M, MUNGAS G.NOFBXTM:a non-toxic, “green” propulsion technology with high performance and low cost:AIAA 2012-5235[R].USA:AIAA,2012.
[2] MUNGAS G, FISHER D J, MUNGAS C, et al.Nitrous Oxide Fuel Blend Mono-propellants:US 2009/0133788 A1[P].2009-05-28.
[3] MUNGAS G, VOZOFF M, RISHIKOF B.NOFBXTM:a new non-toxic, “green” propulsion technology with high performance and low cost:IAC-12-C4.9.10[R].USA:IAC,2012.
[4] TAYLOR R.Safety and performance advantages of nitrous oxide fuel blends(NOFBX)propellants for manned and unmanned spaceflight applications[C]//Proceedings of 5th IAASS Conference on ‘A Safer Space for a Safer World'.Vesailles, France:IAASS,2011.
[5] MUNGAS G, FISHER D J, MUNGAS C, et al.Spark-integerated Propellant Injector Head with Flashback Barrier:US 8230672 B2[P].2012-07-31.
[6] MUNGAS G, FISHER D J, MUNGAS C, et al.Rocket Engine Injector Head with Flashback Barrier:US 8230673 B2[P].2012-07-31.
[7] DOYLE K, MUNGAS G, FISHER D J.Flashback shut-off:US 2011/0005194A1[P].2011-01-13.
[8] MUNGAS G, FISHER D J, LONDON A, et al. Regeneratively cooled porous media jacket:US 20090633770[P].2013-04-09.
[9] WERLING L, PERAKIS N, et al.Experimental investigations based on a demonstrator unit to analyze the combustion process of a nitrous oxide/ethane premixed green bipropellant[C]//5th CEAE Air & Space Conference. Niederlande:CEAS,2015.
[10] WERLING L K, HOCHHEIMER B, BARAL A L, et al.Experimental and numerical analysis of the heat flux occurring in a nitrous oxide/ethene green propellant combustion demonstrator[C]//51st AIAA/SAE/ASEE Joint Propulsion Conference. Virginia:American Institute of Aeronautics and Astronautics,2015.
[11] WERLING L, HAUK A, et al.Pressure drop measurement of porous materials:flashback arrestors for a N2O/C2H4 premixed green propellant:AIAA 2016-5094[R].USA:AIAA,2016.
[12] WERLING L, LAUCK F.Experimental investigation of the ignition, flame propagation and flashback behavior of a premixed green propellant[C]//7th European Conference for Aeronautics and Aerospace Science. Italy:Milano,2017.
[13] WERLING L K, HASSLER M, LAUCK F, et al.Experimental performance analysis(C* & C* efficiency)of a premixed green propellant consisting of N2O and C2H4[C]//53rd AIAA/SAE/ASEE Joint Propulsion Conference. Virginia:American Institute of Aeronautics and Astronautics,2017.
[14] 朱成财, 韩伟.氧化亚氮基单元复合推进剂技术研究述评[J].火箭推进,2016,42(2):79-85.
ZHU C C, HAN W.Review of Nitrous-oxide-based Composite Monopropellants Technology[J].Journal of Rocket Propulsion,2016,42(2):79-85.
[15] 李智鹏,孙海云,蒋榕培,等.乙烯-氧化亚氮层流预混燃烧过程研究[J].火箭推进,2018,44(5):37-42.
LI Z P, SUN H Y, JIANG R P, et al.Study on premixed laminar combustion process of ethylene/nitrous oxide mixture[J].Journal of Rocket Propulsion,2018,44(5):37-42.
[16] 张锋,严宇.气氧/煤油富燃燃气发生器燃烧试验研究[J].推进技术,2016,37(10):1916-1921.
[17] 杜正刚, 高玉闪, 李茂, 等.同轴双剪切气-气喷嘴试验研究[J].推进技术,2010,31(2):170-173.
[18] 王治军, 常新龙, 田干.液体火箭发动机推力室设计[M].北京:国防工业出版社,2014.
[19] 杨立军, 富庆飞.液体火箭发动机推力室设计[M].北京:北京航空航天大学出版社,2013.
相似文献/References:
[1]李智鹏,孙海云,蒋榕培,等.乙烯-氧化亚氮层流预混燃烧过程研究[J].火箭推进,2018,44(05):37.
LI Zhipeng,SUN Haiyun,JIANG Rongpei,et al.Study on premixed laminar combustion process of ethylene/nitrous oxide mixture[J].Journal of Rocket Propulsion,2018,44(03):37.
备注/Memo
收稿日期:2018-12-07
基金项目:国家重点实验室开发基金(6142704040308)
作者简介:张 锋(1981—),男,研究员,研究领域为喷雾与燃烧技术、传热与冷却技术
更新日期/Last Update:
2019-06-30