-
摘要:
根据喷嘴长度和入口边界条件，将液体火箭发动机气液同轴式喷嘴简化为4类：四分之一波长闭管、二分之一波长闭管、四分之一波长开管和二分之一波长开管。采用线性声学理论对喷嘴入口开口率的声学抑制影响进行了研究，得到了入口开口率声学影响规律。结果表明：在标准长度和最佳长度2种条件下，开口率对喷嘴抑制能力的影响差别很大。合理选择开口率和喷嘴长度能够有效提高喷嘴抑制能力。研究结果可为喷嘴长度和入口射流条件优化设计、燃烧室声学振荡抑制提供参考。
Abstract:According to the length and the inlet boundary conditions of injector, the gas-liquid coaxial injectors of liquid rocket engine are simplified into four categories:1/4 wavelength closed tube, 1/2 wavelength closed tube, 1/4 wavelength open tube and 1/2 wavelength open tube. Linear acoustics is adopted to analyze the influence of the inlet opening ratio on the acoustic damping capability of the injector in order to obtain the law of the acoustic influence of opening ratio. It is found that the inlet opening rate has a very different effect on the damping capability of the injector under the conditions of standard length and optimal length. The damping capability can be greatly improved if the inlet opening rate and the length of the injector are chosen reasonably. The research results can provide reference for the optimum design of the length and inlet jet of the injectors, and acoustic damping of the combustion chamber.
-
图 3 无喷嘴燃烧室声学压力响应
Figure 3. Acoustic-pressure responses in combustionchamber without injector
图 6 不同开口率喷嘴内轴向声压振幅变化
Figure 6. Acoustic pressure amplitude variations of injector inaxial direction at different opening rates
-
[1] 哈杰D T,里尔登F H.液体推进剂火箭发动机不稳定燃烧[M].朱宁昌,张宝炯,译.北京:国防工业出版社,1981:15-16.HARRJE D T,REARDON F H.Liquid propellant rocket combustion instability[M].ZHU N C,ZHANG B J,translated.Beijing:National Defend Industry Press,1981:15-16(in Chinese). [2] SOHN C H,KIM S K,KIM Y M.Effects of various baffle designs on acoustic characteristics in combustion chamber of liquid rocket engine[J].KSME International Journal,2004,18(1):145-152. doi: 10.1007/BF03028799 [3] 聂万胜,庄逢辰.声腔应用于液体火箭发动机不稳定燃烧抑制中的特性研究[J].国防科技大学学报,1998,20(2):12-16. http://www.cnki.com.cn/Article/CJFDTOTAL-GFKJ802.003.htmNIE W S,ZHUANG F C.The study of characteristics of resonators used in liquid rocket engines combustion stabilities suppression[J].Journal of National University of Defense Technology,1998,20(2):12-16(in Chinese). http://www.cnki.com.cn/Article/CJFDTOTAL-GFKJ802.003.htm [4] PARK I S,SOHN C H,KIM H J.Acoustic damping enhanced by gaps in baffled injectors in an acoustic chamber[J].Journal of Sound and Vibration,2011,330(12):2747-2757. doi: 10.1016/j.jsv.2010.12.028 [5] 杨V,安德松W E.液体火箭发动机燃烧不稳定性[M].张宝炯,洪鑫,陈杰,译.北京:科学出版社,2001:311-328.VIGOR Y,ANDERSON W E.Liquid rocket engine combustion instability[M].ZHANG B J,HONG X,CHEN J,translated.Beijing:Science Press,2001:311-328(in Chinese). [6] KIM H,SOHN C H.Experimental study of the role of gas-liquid scheme injector as an acoustic resonator in a combustion chamber[J].Journal of Mechanical Science and Technology,2006,20(6):896-904. doi: 10.1007/BF02915952 [7] SOHN C H,PARK I S,KIM S K,et al.Acoustic tuning of gas-liquid scheme injectors for acoustic damping in a combustion chamber of a liquid rocket engine[J].Journal of Sound and Vibration,2007,304(3-5):793-810. doi: 10.1016/j.jsv.2007.03.036 [8] PARK J H,SOHN C H.On optimal design of half-wave rresonators for acoustic damping in an enclosure[J].Journal of Sound and Vibration,2009,319(3-5):807-821. doi: 10.1016/j.jsv.2008.06.049 [9] PARK I S,SOHN C H.Nonlinear acoustic damping induced by a half-wave resonator in an acoustic chamber[J].Aerospace Science and Technology,2010,14(6):442-450. doi: 10.1016/j.ast.2010.04.011 [10] SOHN C H,PARK J H.A comparative study on acoustic damping induced by half-wave,quarter-wave,and Helmholtz resonators[J].Aerospace Science and Technology,2011,15(8):606-614. doi: 10.1016/j.ast.2010.12.004 [11] IM S H,KIM Y J,SOHN C H.Acoustic damping of gas-liquid scheme injectors with a recess in a subscale combustor[J].Journal of Mechanical Science and Technology,2014,28(9):3813-3823. doi: 10.1007/s12206-014-0845-4 [12] KIM S K,CHOI H S,KIM H J.Finite Element analysis for acoustic characteristics of combustion stabilization devices[J].Aerospace Science and Tecnology,2015,42:229-240. doi: 10.1016/j.ast.2015.01.024 [13] WIERMAN M,FELDMAN T,ANDERSON W E.Development of combustion response functions in a subscale high pressure longitudinal combustor:AIAA-2013-3778[R].Reston:AIAA, 2013. [14] 张蒙正,张志涛,杨国华.燃烧室声学特性模拟实验及应用[J].实验技术与管理,2007,24(8):39-42. http://www.cnki.com.cn/Article/CJFDTOTAL-SYJL200708011.htmZHANG M Z,ZHANG Z T,YANG G H.Simulation test and application of chamber acoustic characteristics[J].Experimental Technology and Management,2007,24(8):39-42(in Chinese). http://www.cnki.com.cn/Article/CJFDTOTAL-SYJL200708011.htm [15] 王枫,李龙飞,张贵田.液氧煤油补燃发动机喷注器高频不稳定性的试验研究[J].宇航学报,2012,33(2):260-264. http://www.cnki.com.cn/Article/CJFDTOTAL-YHXB201202018.htmWANG F,LI L F,ZHANG G T.Experimental study on high frequency combustion instability with coaxial injector of staged combustion LOX/kerosene rocket engine[J].Journal of Astronautics,2012,33(2):260-264(in Chinese). http://www.cnki.com.cn/Article/CJFDTOTAL-YHXB201202018.htm [16] 周进,胡小平,黄玉辉,等.液体火箭发动机气液同轴式喷嘴声学特性的实验研究[J].推进技术,1996,17(4):37-41. http://www.cnki.com.cn/Article/CJFDTOTAL-TJJS604.008.htmZHOU J,HU X P,HUANG Y H,et al.An experimental study on acoustic characteristics of gas-liquid coaxial injector of liquid rocket engine[J].Journal of Propulsion Technology,1996,17(4):37-41(in Chinese). http://www.cnki.com.cn/Article/CJFDTOTAL-TJJS604.008.htm -
下载:
点击查看大图
计量
- 文章访问数: 754
- HTML全文浏览量: 95
- PDF下载量: 371
- 被引次数: 0
