煤油/氧气超音速射流特性研究
|
摘要
为了获得煤油/氧气超音速射流场的参数分布,将航空煤油和高压氧气在燃烧室内混合,煤油被氧气雾化后形成混合液雾,将液雾点火并通过拉瓦尔喷管加速后喷出,形成高温的超音速射流。采用数值计算和试验测试相结合的方法对超音速射流的射流场开展研究。经过计算获得射流出口处轴心线上的速度和温度的分布规律;利用FLUENT仿真计算软件并结合边界条件,获得整个射流场的速度和温度的仿真计算结果。试验中,首先采用金属熔点法对射流场的温度分布进行验证实验,然后在射流中加入三氧化二铝粉末,采用Spray watch在线粒子测试仪测量距离出口不同距离处射流的速度和温度场的分布;测试时改变航空煤油和高压氧气的输入混合比,观察在不同的富氧度下射流场中各参数的变化。结果表明,射流出口的温度约为2 800K左右,速度约为2 150 m/s左右;当距离喷管出口的距离增大时,射流的温度和速度的分布呈抛物线形急剧下降;当混合液雾的富氧度增大时,射流流场中同一点的温度和速度值都随之降低。
The aviation kerosene and O_2 were ignited in the chamber in order to obtain the distribution characteristics of the high velocity jet,which was accelerated and sprayed from the exit. The distribution characteristics of the temperature and velocity on the axis at the exit were obtained by calculation The distribution of the field was obtained by FLUENT numerical simulations. Measuring the temperature and velocity at different distances with particle tester and metal-melt method,the jet characteristics will change with the change of kerosene O_2 ratio The results show that the temperature is about 2 800 K and the velocity is about 2 150 m/s at the exit. The temperature and velocity reduce with the distance increase What's more,with the increase of oxygen-enriched degree,the temperature and velocity in the jet field reduce obviously.
The aviation kerosene and O_2 were ignited in the chamber in order to obtain the distribution characteristics of the high velocity jet,which was accelerated and sprayed from the exit. The distribution characteristics of the temperature and velocity on the axis at the exit were obtained by calculation The distribution of the field was obtained by FLUENT numerical simulations. Measuring the temperature and velocity at different distances with particle tester and metal-melt method,the jet characteristics will change with the change of kerosene O_2 ratio The results show that the temperature is about 2 800 K and the velocity is about 2 150 m/s at the exit. The temperature and velocity reduce with the distance increase What's more,with the increase of oxygen-enriched degree,the temperature and velocity in the jet field reduce obviously.
引文
[1]李斌,谭永华.液氧/煤油富氧补燃发动机[J].火箭推进,2003,29(2):1-6.
[2] READ R W,ROGERSON J W,HOCGREB S. Relight imaging at low temperature, low pressure conditions:AIAA2008-0957[R].[S. l.]:AIAA,2008.
[3] Vasu S S,Davidon D F. Jet fuel ignition delay times:shock tube experiments over wide conditions and surrogate model predictions[J]. Combustion and Flame,2008,152(1/2):125-143.
[4]雷向东,余协正,杨京军,等.氧气/煤油点火装置高空点火试验研究[J].火箭推进,2014,40(6):37-43.
[5]梁金虎,王苏,张灿,等. RP-3航空煤油点火特性研究[J].力学学报,2014,46(3):352-360.
[6]吴宝元,张民庆.液氧/煤油富氧预燃室的理论分析和试验研究[J].推进技术,1999,20(5):11-16.
[7]雷震,代玉东.液氧/煤油发动机试车热敏电阻测温技术[J].火箭推进,2003,29(4):35-39.
[8]王爱玲,吴建军.气氧/煤油发动机电点火技术研究[J].上海航天,2006(6):14-17.
[9]赵正社.液氧/煤油发动机试验低温测量系统的设计与实现[J].火箭推进,2001,27(2):36-41.
[10]张福祥.火箭燃气射流动力学[M].哈尔滨:哈尔滨工程大学出版社,2004.
[11]曹再勇,蔡体敏,谭永华.富氧燃气发生器三维燃烧流场的数值模拟[J].西北工业大学学报,2005,23(5):557-561.
[12]翟鹏,杨月诚.基于FLUENT的烧蚀喷枪两相流流场数值模拟[J].弹箭与制导学报,2012,32(3):133-136.
[13]程钰锋,聂万胜,丰松江.氢氧火箭发动机不稳定燃烧数值研究[J].装备指挥技术学院学报,2009,20(4):69-73.
[14]饶琼,周香林,张济山,等.超音速喷涂技术及其应用[J].热加工工艺,2004(10):49-52.
[15]于永志.固体火箭发动机尾焰温度场特性研究[D].沈阳:沈阳理工大学,2016.
[2] READ R W,ROGERSON J W,HOCGREB S. Relight imaging at low temperature, low pressure conditions:AIAA2008-0957[R].[S. l.]:AIAA,2008.
[3] Vasu S S,Davidon D F. Jet fuel ignition delay times:shock tube experiments over wide conditions and surrogate model predictions[J]. Combustion and Flame,2008,152(1/2):125-143.
[4]雷向东,余协正,杨京军,等.氧气/煤油点火装置高空点火试验研究[J].火箭推进,2014,40(6):37-43.
[5]梁金虎,王苏,张灿,等. RP-3航空煤油点火特性研究[J].力学学报,2014,46(3):352-360.
[6]吴宝元,张民庆.液氧/煤油富氧预燃室的理论分析和试验研究[J].推进技术,1999,20(5):11-16.
[7]雷震,代玉东.液氧/煤油发动机试车热敏电阻测温技术[J].火箭推进,2003,29(4):35-39.
[8]王爱玲,吴建军.气氧/煤油发动机电点火技术研究[J].上海航天,2006(6):14-17.
[9]赵正社.液氧/煤油发动机试验低温测量系统的设计与实现[J].火箭推进,2001,27(2):36-41.
[10]张福祥.火箭燃气射流动力学[M].哈尔滨:哈尔滨工程大学出版社,2004.
[11]曹再勇,蔡体敏,谭永华.富氧燃气发生器三维燃烧流场的数值模拟[J].西北工业大学学报,2005,23(5):557-561.
[12]翟鹏,杨月诚.基于FLUENT的烧蚀喷枪两相流流场数值模拟[J].弹箭与制导学报,2012,32(3):133-136.
[13]程钰锋,聂万胜,丰松江.氢氧火箭发动机不稳定燃烧数值研究[J].装备指挥技术学院学报,2009,20(4):69-73.
[14]饶琼,周香林,张济山,等.超音速喷涂技术及其应用[J].热加工工艺,2004(10):49-52.
[15]于永志.固体火箭发动机尾焰温度场特性研究[D].沈阳:沈阳理工大学,2016.