含铝金属化浆体推进剂火箭发动机燃烧性能试验研究
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摘要
为研究含铝浆体推进剂的燃烧特性,对浆体推进剂模型火箭发动机开展了一系列试验研究。分别将质量分数为21%的纳米铝粉颗粒以及质量分数为12%的氢化铝复合粒子加入到JP-10燃料中,对比分析了浆体燃料与纯净燃料在燃烧性能方面的差异。燃烧试验的氧燃比为1.6~2.0。试验结果表明:与纯净JP-10燃料相比,加入金属颗粒的JP-10浆体燃料在雾化和燃烧过程中产生了严重的结块聚集效应,导致其燃烧效率与质量比冲明显降低,而由于浆体燃料密度远大于纯净JP-10燃料,含纳米铝颗粒的浆体燃料的密度比冲相比于纯净JP-10燃料有大幅提高,提高幅度为5.5%~14.6%。试验还发现浆体燃料的点火延迟略低于纯净JP-10燃料,金属颗粒的加入对推进剂点火性能有积极的影响。试验中采集了喷管出口的固体燃烧产物并进行了XRD,EDS,SEM,TEM等多种手段分析,发现浆体燃料中铝的氧化率约为64%~74%,颗粒团聚现象明显,主要呈球形,尺寸分布不均,约为500nm~3μm。
A series of model rocket engine combustion experiments were conducted in order to investigate the combustion characteristics of slurry propellant containing aluminum particles. The fuels used were traditional liquid JP-10,JP-10-based slurry with 21-wt% loadings of nano-sized aluminum particles and JP-10-based slurry with 12-wt% loadings of micro-sized aluminum hydride composite particles. The differences in the combustion characteristic between the slurry and the pure fuel were analyzed. The oxygen-to-fuel ratios were set to be 1.6~2.0. The results showed that compared with pure JP-10,the JP-10-based slurries presented obviously lower mass specific impulse and combustion efficiency,due to the special aggregation phenomenon of metal particles in the process of atomization and combustion. However,the JP-10-based slurries achieved a higher density specific impulse by 5.5% to 14.6% compared to pure JP-10,because the metalized propellant has higher density.It was also found that the ignition delay of the slurry fuels was slightly shorter than that of the pure JP-10 fuel and it proved that the addition of metal particles has a positive effect on the propellant ignition performance. In addition,condensed combustion products are sampled in the jet plume behind the exit nozzles to analyze the components of products. By means of the energy dispersive spectrometer(EDS),X-ray diffraction(XRD),scanning electron microscope(SEM),and transmission electron microscope(TEM),it was found that 64%~74% aluminum was oxidized in the tests,and the solid particles are mainly spherical and in size of 500 nm~3 mm.
A series of model rocket engine combustion experiments were conducted in order to investigate the combustion characteristics of slurry propellant containing aluminum particles. The fuels used were traditional liquid JP-10,JP-10-based slurry with 21-wt% loadings of nano-sized aluminum particles and JP-10-based slurry with 12-wt% loadings of micro-sized aluminum hydride composite particles. The differences in the combustion characteristic between the slurry and the pure fuel were analyzed. The oxygen-to-fuel ratios were set to be 1.6~2.0. The results showed that compared with pure JP-10,the JP-10-based slurries presented obviously lower mass specific impulse and combustion efficiency,due to the special aggregation phenomenon of metal particles in the process of atomization and combustion. However,the JP-10-based slurries achieved a higher density specific impulse by 5.5% to 14.6% compared to pure JP-10,because the metalized propellant has higher density.It was also found that the ignition delay of the slurry fuels was slightly shorter than that of the pure JP-10 fuel and it proved that the addition of metal particles has a positive effect on the propellant ignition performance. In addition,condensed combustion products are sampled in the jet plume behind the exit nozzles to analyze the components of products. By means of the energy dispersive spectrometer(EDS),X-ray diffraction(XRD),scanning electron microscope(SEM),and transmission electron microscope(TEM),it was found that 64%~74% aluminum was oxidized in the tests,and the solid particles are mainly spherical and in size of 500 nm~3 mm.
引文
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[20]陈克海,鲁统洁,韦伟,等.三氢化铝含量对HD-01复配燃料性能的影响[J].化学推进剂与高分子材料,2016,14(5):44-46.
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[22]Taylo B N,Kuyatt C E,Brown R H,et al.Guidelines for Evaluating and Expressing the Uncertainty of NIST Measurement Results[M].Washington DC:NIST Technical Note 1297,1994.
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[3]高东磊,张炜,朱慧,等.纳米铝粉在复合推进剂中的应用[J].固体火箭技术,2007,30(5):420-423.
[4]禹天福,甄江涛.美国液体推进剂标准化发展状况[J].航天标准化,2009,(2):28-32.
[5]吴志坚.金属化胶体推进剂性能研究[J].导弹与航天运载技术,2006,(3).
[6]代玉东,魏敬.美国凝胶推进剂研究[J].火箭推进,2003,29(6):40-44.
[7]王宝成,李鑫,赵凤起.凝胶推进剂研究进展[J].化学推进剂与高分子材料,2015,13(1):1-6.
[8]Gordon L J,Lee J B.Metals as Fuels in Multicomponent Propellants[J].ARS Journal,1962,32(4):600-606.
[9]Tepper F,Kaledin L A.Nano Aluminum as a Combustion Accelerant for Kerosene in Air Breathing Systems[R].AIAA 2001-16395.
[10]Zurawski R L,Green J M.An Evaluation of Metallized Propellants Based on Vehicle Performance[R].AIAA1987-1773.
[11]Bryan P,James S Z.Metallized Gelled Propellants-Oxygen/RP-1/Aluminum Rocket Heat Transfer and Combustion Measurements[R].AIAA 96-2622.
[12]Ellison R,Hall T,Moser M D.Gelled RP-1 Nanophase Aluminum Propellant[R].AIAA 2003-4498.
[13]Mordosky J W.Spray Combustion of Gelled RP-1 Propellants Containing Nano-Sized Aluminum Particles in Rocket Engine Conditions[R].AIAA 2001-3274.
[14]Mueller D C,Turns S R.Theoretical Effects of Aluminum Gel Propellant Secondary Atomization on Rocket Engine Performance[J].Journal of Propulsion and Power,1996,12(3):591-597.
[15]Luo Yu,Xu Xu.Combustion of JP-10-Based Slurry with Nanosized Aluminum Additives[J].Journal of Propulsion and Power,2016,32(5):1167-1177.
[16]Chakraborty P,Zachariah M R.Do Nano Energetic Particles Remain Nano-Sized During Combustion?[J].Combustion and Flame,2014,161(5):1408-1416.
[17]Negri M,Ciezki H K.Combustion of Gelled Propellants Containing Micro Sized and Nano Sized Aluminum Particles[J].Journal of Propulsion and Power,2015,31(1):400-407.
[18]邹吉军,郭成,张香文,等.航天推进用高密度液体碳氢燃料:合成与应用[J].推进技术,2014,35(10):1419-1425.(ZOU Ji-jun,GUO Cheng,ZHANG Xiang-wen,et al.High-Density Liquid Hydrocarbon Fuels for Aerospace Propulsion:Synthesis and Application[J].Journal of Propulsion Technology,2014,35(10):1419-1425.)
[19]鄂秀天凤,彭浩,邹吉军,等.含有纳米铝颗粒的高密度悬浮燃料研究[J].推进技术,2016,37(5):974-978.(E Xiu-tian-feng,PENG Hao,ZOU Ji-jun,et al.Study on Al NPs-Containing Suspension as HighDensity Liquid Fuel[J].Journal of Propulsion Technology,2016,37(5):974-978.)
[20]陈克海,鲁统洁,韦伟,等.三氢化铝含量对HD-01复配燃料性能的影响[J].化学推进剂与高分子材料,2016,14(5):44-46.
[21]刘明星,何金选,曹一林.三氢化铝的合成及性能研究[J].固体火箭技术,2008,31(1):75-78.
[22]Taylo B N,Kuyatt C E,Brown R H,et al.Guidelines for Evaluating and Expressing the Uncertainty of NIST Measurement Results[M].Washington DC:NIST Technical Note 1297,1994.