复合推进剂中铝粉粒度对分布燃烧响应和粒子阻尼特性影响
|
摘要
针对不同初始铝粉粒度的含铝复合推进剂,对其燃烧产物粒子阻尼特性和铝粒子分布燃烧响应特性进行了试验研究。试验结果表明:粒子阻尼的大小取决于流场中的凝相燃烧产物粒径分布和振荡频率,与推进剂中铝粉初始粒度基本无关;粒子阻尼预估方面,采用单一粒径预估的阻尼值与实际测量的阻尼值相比,仍存在一定的误差(>10%),需要进一步改进;分布燃烧响应方面,在同一振荡频率范围内,分布燃烧响应特性与复合推进剂中初始铝粉粒度有关,即初始铝粉粒度越大,在燃烧过程中产生的分布燃烧增益越大,这对于发动机燃烧的稳定性是十分不利的。
According to the aluminized composite propellants with different initial particle sizes,the characteristics of the particle damping of condensed phase combustion products and the distribution combustion response were researched. The result shows that,particle damping is dependent on the particle size distribution of the condensed phase combustion products and the oscillation frequency,which is reasonably insensitive to the initial aluminum particle sizes. On the aspect of estimating the particle damping,the particle damping computed using the mono-sized particles were different from the value in the experiment,with the relative error more than10 percent. Thus,further improvement on the prediction method is needed. On the aspect of distributed combustion response,the distributed combustion response is sensitive to the initial aluminum particle sizes in the same oscillation frequency,that is,the bigger the sizes of the initial aluminum particles are,the higher the combustion driven in the combustion,which is not good in solid rocket motor from a combustion instability point of view.
According to the aluminized composite propellants with different initial particle sizes,the characteristics of the particle damping of condensed phase combustion products and the distribution combustion response were researched. The result shows that,particle damping is dependent on the particle size distribution of the condensed phase combustion products and the oscillation frequency,which is reasonably insensitive to the initial aluminum particle sizes. On the aspect of estimating the particle damping,the particle damping computed using the mono-sized particles were different from the value in the experiment,with the relative error more than10 percent. Thus,further improvement on the prediction method is needed. On the aspect of distributed combustion response,the distributed combustion response is sensitive to the initial aluminum particle sizes in the same oscillation frequency,that is,the bigger the sizes of the initial aluminum particles are,the higher the combustion driven in the combustion,which is not good in solid rocket motor from a combustion instability point of view.
引文
[1]刘佩进,白俊华,杨向明,等.固体火箭发动机燃烧室凝相粒子的收集与分析[J].固体火箭技术,2008,31(5):461-463.
[2]张宏安,叶定友,侯晓,等.含铝复合推进剂燃烧场凝相微粒分布实验研究[J].固体火箭技术,2001,24(1):24-27.
[3]王宁飞,陈龙,赵崇信,等.固体火箭燃烧室内微粒分布的实验研究[J].推进技术,1995,16(4):24-27.(WANG Ning-fei,CHEN Long,ZHAO Chun-xin,et al.An Experimental Study on Distribution of Particulates in Solid Rocket Motors[J].Journal of Propulsion Technology,1995,16(4):24-27.)
[4]陈晓龙,何国强,刘佩进.固体火箭发动机燃烧不稳定的影响因素分析和最新研究进展[J].固体火箭技术,2009,32(6):600-605.
[5]谢蔚民.固体火箭发动机不稳定燃烧[M].西安:航空教材编审组,1984.
[6]Blomshield F S,Beckstead M W.Combustion Instability Additive Investigation[R].AIAA 99-2226.
[7]王宁飞,苏万兴,李军伟,等.固体火箭发动机中铝粉燃烧研究概述[J].固体火箭技术,2011,34(1):61-66.
[8]Blomshield F S,Suong Nguyen,Heather Matheke.Acoustic Particle Damping of Propellants Containing Ultra-Fine Aluminum[R].AIAA 2004-3722.
[9]赵志博,刘佩进,张少悦,等.NEPE高能推进剂凝相燃烧产物的特征分析[J].推进技术,2010,31(1):69-73.(ZHAO Zhi-bo,LIU Pei-jin,ZHANG Shaoyue,et al.Combustion Peculiarity of Condensed-Products of NEPE Propellant[J].Journal of Propulsion Technology,2010,31(1):69-73.)
[10]刘佩进,金秉宁,李强.战术导弹固体发动机燃烧不稳定研究概述[J].固体火箭技术,2012,35(4):446-449.
[11]Gallier S,Radenac E,Godfroy F.Thermoacoustic Instabilities in Solid Rocket Motors[R].AIAA 2009-5252.
[12]Gallier S,Godfroy F.Aluminum Combustion Driven Instabilities in Solid Rocket Motors[J].Journal of Propulsion and Power,2009,25(2):509-521.
[13]刘佩进,齐宗满,金秉宁,等.两种含铝复合推进剂压强耦合响应的试验对比[J].固体火箭技术,2013,36(1):83-88.
[14]Culick F E C.T-Burner Testing of Metallized Solid Propellants[R].ADA:001665,1974.
[15]Wasistho B,Najjar F M.Effect of Turbulence and Particle Combustion on Solid Rocket Motor Instabilities[R].AIAA 2005-4345.
[16]方丁酉.两相流动力学[M].长沙:国防科技大学出版社,1988.
[2]张宏安,叶定友,侯晓,等.含铝复合推进剂燃烧场凝相微粒分布实验研究[J].固体火箭技术,2001,24(1):24-27.
[3]王宁飞,陈龙,赵崇信,等.固体火箭燃烧室内微粒分布的实验研究[J].推进技术,1995,16(4):24-27.(WANG Ning-fei,CHEN Long,ZHAO Chun-xin,et al.An Experimental Study on Distribution of Particulates in Solid Rocket Motors[J].Journal of Propulsion Technology,1995,16(4):24-27.)
[4]陈晓龙,何国强,刘佩进.固体火箭发动机燃烧不稳定的影响因素分析和最新研究进展[J].固体火箭技术,2009,32(6):600-605.
[5]谢蔚民.固体火箭发动机不稳定燃烧[M].西安:航空教材编审组,1984.
[6]Blomshield F S,Beckstead M W.Combustion Instability Additive Investigation[R].AIAA 99-2226.
[7]王宁飞,苏万兴,李军伟,等.固体火箭发动机中铝粉燃烧研究概述[J].固体火箭技术,2011,34(1):61-66.
[8]Blomshield F S,Suong Nguyen,Heather Matheke.Acoustic Particle Damping of Propellants Containing Ultra-Fine Aluminum[R].AIAA 2004-3722.
[9]赵志博,刘佩进,张少悦,等.NEPE高能推进剂凝相燃烧产物的特征分析[J].推进技术,2010,31(1):69-73.(ZHAO Zhi-bo,LIU Pei-jin,ZHANG Shaoyue,et al.Combustion Peculiarity of Condensed-Products of NEPE Propellant[J].Journal of Propulsion Technology,2010,31(1):69-73.)
[10]刘佩进,金秉宁,李强.战术导弹固体发动机燃烧不稳定研究概述[J].固体火箭技术,2012,35(4):446-449.
[11]Gallier S,Radenac E,Godfroy F.Thermoacoustic Instabilities in Solid Rocket Motors[R].AIAA 2009-5252.
[12]Gallier S,Godfroy F.Aluminum Combustion Driven Instabilities in Solid Rocket Motors[J].Journal of Propulsion and Power,2009,25(2):509-521.
[13]刘佩进,齐宗满,金秉宁,等.两种含铝复合推进剂压强耦合响应的试验对比[J].固体火箭技术,2013,36(1):83-88.
[14]Culick F E C.T-Burner Testing of Metallized Solid Propellants[R].ADA:001665,1974.
[15]Wasistho B,Najjar F M.Effect of Turbulence and Particle Combustion on Solid Rocket Motor Instabilities[R].AIAA 2005-4345.
[16]方丁酉.两相流动力学[M].长沙:国防科技大学出版社,1988.