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Powder engine is one kind of new concept engines with multiple ignition capability and thrust modulation function. Powder filling is an important process of the powder engine tests. The powder pneumatic filling experiments were carried out to investigate the effects of the filling position of the powder collection box and the mass flow rate of fluidization gas on the stability and performance of powder pneumatic filling. It’s found that large mass flow rate of fluidization gas contributes to stability of powder pneumatic filling, but its volume efficiency of powder filling is the lowest, only 68.1%, but it’s 93.9% when the mass flow rate of fluidization gas is small. Compared with the vertical inlet of end cap, tangential inlet on the cylinder wall makes the powder uniformity better. In the pneumatic filling mode, the powder bulk density in the collection box is greater than the bulk density in the powder tank. In addition, the mass of powder calculated by position displacement is always larger than the mass of powder measured by the electronic balance. It indicates powder bulk density in tank is constantly changing during the powder pneumatic filling experiments. The actual powder bulk density in the powder tank is calculated by a model established in this paper, it’s found that when the mass flow rate of fluidization gas is low, the bulk density of the powder in the tank is increased first and then decreased, and the final bulk density is less than the initial value. While the mass flow rate of fluidization gas is high, powder bulk density in the tank is first increased, then decreased, then increased and then decreased, and the final bulk density is greater than the initial value. The compression mechanism of powder bulk density in the tank is similar to the motion law of the damper spring vibrator when it is forced to vibrate. It can be described by the damped second-order system response function. When the mass flow rate of fluidization gas is small, the damping coefficient of the system is smaller. While the mass flow rate of fluidization gas is large, the damping coefficient is larger and is variable.
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Keywords:
- powder pneumatic filling /
- powder filling performance /
- compression mechanism of powder /
- damped second-order system
[1] 李悦, 胡春波, 胡加明, 朱小飞, 张力锋, 李超 2018 推进技术, 39 1681
Li Y, Hu C B, HU J M, Zhu X F, Zhang L F, Li C 2018 J. Propul. Technol. 39 1681
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Wang L, Li Y Z, Ma Y, Xie F S 2016 J. Aerosp. Power 31 2002
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Li S J, Zhou X J 1992 Pneumatic Conveying Theory and Application (Beijing: Mechanical Industry Press) pp111−119 (in Chinese)
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图 1 单一粉末样品粒度分布
Figure 1. Particle size distribution of single powder sample
图 2 混合粉粒度分布
Figure 2. Particle size distribution of mixed powder sample
图 3 粉末气力加注系统
Figure 3. Powder pneumatic filling system.
图 4 粉末供给系统
Figure 4. Powder feeding system.
图 5 集粉箱
Figure 5. Powder collection box.
图 6 不同加注方式对工作参数的影响: (a)工况1#; (b)工况2#; (c) 工况3#
Figure 6. Working parameters of different tests: (a) Test 1#; (b) test 2#; (c) test 3#
图 7 不同加注方式下的粉末加注质量曲线
Figure 7. Mass curves measured by electronic balance at different filling methods.
图 8 集粉箱内的粉末压实现象
Figure 8. Compacted powder in collection box.
图 9 集粉箱内粉末粒度均匀性: (a)工况1#; (b)工况2#; (c)工况3#
Figure 9. Uniformity of powder in collection box: (a) Test 1#; (b) test 2#; (c) test 3#.
图 10 位移换算与天平测量质量曲线
Figure 10. Mass curves converted by position displacement and measured by electronic balance.
图 11 储箱内粉末堆积密度变化曲线: (a) 工况1#; (b) 工况 2#
Figure 11. Powder bulk density in tank of test 1# and test 2#: (a) Test 1#; (b) test 2#.
表 1 实验工况
Table 1. Experiment conditions.
工况 加注位置 流化气量/(g·s–1) 1# 壁面切向 3.2 2# 壁面切向 6.4 3# 垂直端盖 3.2 
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表 2 部分加注性能参数
Table 2. Some performance parameters of powder filling
工况 $t{\rm{/s}}$ $m{\rm{/g}}$ ${\bar {\dot m}}/({\rm{g}} \cdot {{\rm{s}}^{ - 1}}{\rm{)}}$ $H{\rm{/mm}}$ ${\rho _{\rm{c}}}{\rm{/(g}} \cdot {\rm{c}}{{\rm{m}}^{{\rm{ - 3}}}}{\rm{)}}$ $\eta $ 1# 70 1316 18.8 240.5 1.101 93.9% 2# 77 1002 13 174.3 1.142 68.1% 3# 286 1381 4.83 244.5 1.127 95.5%
DownLoad: CSV
表 3 工况1#和工况2#下二阶系统参数
Table 3. Second-order system parameters of test 1# and test 2#.
系统参数 ${\rho _{\min }}$ $K$ $\zeta $ ${\omega _{\rm{n}}}$ $\tau $ 备注 工况1# 874 165 0 0.095 –18.0 — 工况2# 1031 83 0.1 0.090 –6.5 $t$ ≤ 38 s 1031 107 0.38 0.100 14.0 $t$ > 38 s
DownLoad: CSV
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[1] 李悦, 胡春波, 胡加明, 朱小飞, 张力锋, 李超 2018 推进技术, 39 1681
Li Y, Hu C B, HU J M, Zhu X F, Zhang L F, Li C 2018 J. Propul. Technol. 39 1681
[2] 胡旭, 徐义华, 王洪远, 曾卓雄 2014 兵器装备工程学报 35 133
Google Scholar
Hu X, Xu Y H, Wang H Y, Zeng Z X 2014 J. Ordnance Equip. Eng. 35 133
Google Scholar
[3] Li Y, Hu C B, Deng Z, Li C, Sun H J, Cai Y P 2017 Acta Astronaut. 133 455
Google Scholar
[4] Li C, Hu C B, Xin X, Li Y, Sun H J 2016 Acta Astronaut. 129 74
Google Scholar
[5] 杨建刚, 胡春波, 邓哲, 朱小飞 2017 火炸药学报 40 36
Yang J G, Hu C B, Deng Z, Zhu X F 2017 Chin. J. Explos. Propell. 40 36
[6] 王磊, 厉彦忠, 马原, 谢福寿 2016 航空动力学报 31 2002
Wang L, Li Y Z, Ma Y, Xie F S 2016 J. Aerosp. Power 31 2002
[7] 李诗久, 周晓君 1992 气力输送理论与应用 (北京:机械工业出版社) 第111−119页
Li S J, Zhou X J 1992 Pneumatic Conveying Theory and Application (Beijing: Mechanical Industry Press) pp111−119 (in Chinese)
[8] Loftus H, Montanino L, Bryndle R 1972 8th American Institute of Aeronautics and Astronautics Conference New Orleans, America, November 29−December 1, 1972 p1162
[9] Meyer, Mike L 1993 30th Joint Army-Navy-NASA-Air Force Combustion Subcommittee Meeting Monterey, America, November 15−19, 1993 p13
[10] Xia Z X, Shen H J, Hu J X, Liu B 2008 44th American Institute of Aeronautics and Astronautics Conference Hartford, America, July 21−23, 2008 p5131
[11] Goroshin S, Higgins A, Kamel M 2001 37th American Institute of Aeronautics and Astronautics Conference Salt Lake City, America, July 8−11, 2001 p3919
[12] Ramjet, Scramjet and PDE, ONERA http://www.onera. fr/sites/default/files/ressources_documentaires/cours-exposes-conf/ramjet-scramjet-and-pde-an-introduction. pdf)[2019-11-14]
[13] Goroshin S, Higgins A, Lee J 1999 35th American Institute of Aeronautics and Astronautics Conference Los Angeles, America, June 20−24, 1999 p2408
[14] Sun H J, Hu C B, Zhu X F, Yang J G 2017 Exp. Therm. Fluid Sci 83 231
Google Scholar
[15] J.W. Burr, H.D. Fricke and M.G. Sobieniak 1974 US Patent 3 812 671
[16] 杨晋朝, 夏智勋, 胡建新, 孔龙飞 2013 固体火箭术技术 36 37
Yang J C, Xia Z X, Hu J X, Kong L F 2013 J. Solid Rocket Technol. 36 37
[17] Sun H J, Hu C B, Zhang T, Deng Z 2016 Appl. Therm. Eng. 102 30
Google Scholar
[18] Huang J, Xu S, Yi H, Hu S 2014 Powder Technol. 268 86
Google Scholar
[19] 郝刚领, 许巧平, 李先雨, 王伟国 2019 68 126101
Google Scholar
Hao G L, Xu Q P, Li X Y, Wang W G 2019 Acta Phys. Sin. 68 126101
Google Scholar
[20] Misra C, Kim S, Shen S, Sioutas C 2002 J. Aerosol Sci. 33 735
Google Scholar
[21] Gu X F, Song J F, Wei Y D 2016 Powder Technol. 299 217
Google Scholar
[22] Sibanda V, Greenwood R W, Seville J P K 2001 Powder Technol. 118 193
Google Scholar
[23] Gupta R, Gidaspow D, Wasan D T 1993 Powder Technol. 75 79
Google Scholar
[24] Amyotte P R, Eckhoff R K 2010 J. Chem. Health Safe. 17 15
Google Scholar
[25] Yerazunis S, Cornell S W, Wintner B 1965 Nature 207 835
Google Scholar
[26] 朱小飞, 胡春波, 杨建刚, 邓哲 2019 西北工业大学学报 37 20
Zhu X F, Hu C B, Yang J G, Li Y, Liu S N, Deng Z 2019 J. Northwest Polytech. Univ. 37 20
[27] 张权义, 彭政, 何润, 刘锐, 陆坤权, 厚美瑛 2007 56 4708
Google Scholar
Zhang Q Y, Peng Z, He R, Liu R, Lu K Q, Hou M Y 2007 Acta Phys. Sin. 56 4708
Google Scholar
[28] 赵子渊, 李昱君, 王富帅, 张祺, 厚美瑛, 李文辉, 马钢 2018 67 104502
Google Scholar
Zhao Z Y, Li Y J, Wang F S, Zhang Q, Hou M Y, Li W H, Ma G 2018 Acta Phys. Sin. 67 104502
Google Scholar
[29] 李智峰, 彭政, 蒋亦民 2014 63 104503
Google Scholar
Li Z F, Peng Z, Jiang Y M 2014 Acta Phys. Sin. 63 104503
Google Scholar
[30] 杨林, 胡林, 张兴刚 2015 64 134502
Google Scholar
Yang L, Hu L, Zhang X G 2015 Acta Phys. Sin. 64 134502
Google Scholar
[31] 张兴刚, 戴丹 2017 66 204501
Google Scholar
Zhang X G, Dai D 2017 Acta Phys. Sin. 66 204501
Google Scholar
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