Experiment on combustion characteristics of U-bend pulse detonation combustor under high temperature inlet stream
-
摘要: 为了获得高温来流下气/液两相多循环U型脉冲爆震燃烧室(U-PDC)的燃烧特性,使用汽油/空气为燃料和氧化剂开展了相关试验研究。结果表明:当来流温度为373 K,U-PDC能够在15~38 Hz范围内稳定工作,且随着工作频率提高爆燃向爆震转变(DDT)距离缩短;在室温条件下、工作频率为15~25 Hz时,未能形成充分发展爆震波,表明高温来流可促进DDT过程。在室温条件下、工作频率为15~25 Hz时,由于U型爆震弯段内可燃混气分布不均匀,U型爆震弯段外侧监测到火焰的时间晚于U型弯段出口,当来流温度升至373 K后该现象明显改善。此外,U-PDC的点火起爆时间在3~10 ms内,且点火延迟时间是影响点火起爆时间的主要因素;U-PDC工作频率相同、来流温度从室温升高至373 K或来流温度相同、U-PDC工作频率提高时,波速随之提高,点火起爆时间缩短。
-
关键词:
- 脉冲爆震 /
- U型脉冲爆震燃烧室 /
- 高温来流 /
- DDT(爆燃向爆震转变)距离 /
- 点火起爆时间
Abstract: In order to obtain the combustion characteristics of gas-liquid two-phase multi-cycle U-bend pulse detonation combustor (U-PDC) under high temperature inlet stream,experimental research was carried out by using gasoline and air as fuel and oxidant.The results indicated that the U-PDC can achieve stable operation at the working frequency of 15-38 Hz when the inlet temperature was 373 K,and the deflagration to detonation transition (DDT) distance was shortened when the working frequency increased.When the working frequency was 15-25 Hz,the detonation initiation failed at room temperature.The results showed that high temperature inflow can promote the DDT process.At room temperature and working frequency of 15-25 Hz,due to the uneven distribution of combustible gas in the U-bend detonation tube,the time when the flame was detected outside of the U-bend detonation tube was later than the exit of the U-bend detonation tube.When the inflow temperature increased to 373 K,the phenomenon was obviously improved.In addition,the ignition time of U-PDC was within 3-10 ms,which was greatly affected by ignition delay time.When the working frequency of U-PDC was the same and the inlet stream temperature raised from room temperature to 373 K,the wave velocity increased,and the ignition time decreased. -
[1] 严传俊,范玮,郑龙席,等.脉冲爆震发动机原理及关键技术[M].西安:西北工业大学出版社,2005. [2] 郑龙席,王治武,黄希桥,等.脉冲爆震涡轮发动机技术[M].西安:西北工业大学出版社,2019. [3] 郑龙席,卢杰,严传俊,等.脉冲爆震涡轮发动机研究进展[J].航空动力学报,2014,29(5):993-1000. [4] 李晓丰,郑龙席,邱华,等.两相脉冲爆震涡轮发动机原理性试验[J].航空动力学报,2013,28(12):2731-2736. [5] KAILASANATH K.Recent developments in the research on pulse detonation engines[J].AIAA Journal,2003,41(2):145-159. [6] 王凌羿,郑龙席,黄康,等.回流型脉冲爆震燃烧室工作特性分析[J].推进技术,2021,42(4):898-905. [7] JEFFREY G,VENKAT T,ANTHONY D.System-level performance estimation of a pulse detonation based hybrid engine[J].Journal of Engineering for Gas Turbine and Power 2008,130(1):1-8. [8] LI Xiaofeng,ZHENG Longxi,QIU Hua,et al.Experimental investigation on the power extraction of a turbine driven by a pulse detonation combustor[J].Chinese Journal of Aeronautics,2013,26(6):1353-1359. [9] WILLIAM H H,DAVID T P.Thermodynamic cycle analysis of pulse detonation engines[J].Journal of Propulsion and Power ,2002,18(1):68-76. [10] HELFRICH T M,SCHAUER F R.Ignition and detonation-initiation characteristics of hydrogen and hydrocarbon fuels in a PDE[R].Reno,US:the 45th AIAA Aerospace Sciences Meeting and Exhibit,2007. [11] FROLOV S M,AKSENOV V S,SHAMSHIN I O.Shock wave and detonation propagation through U-bend tubes[J].Proceedings of the Combustion Institute,2007,31(2):2421-2428. [12] FROLOV S M,AKSENOV V S,SHAMSHIN I O.Initiation of gaseous detonation in tubes with sharp U-bends[J].Doklady Physical Chemistry,2008,418(5):642-646. [13] FROLOV S M,AKSENOV V S,SHAMSHIN I O.Reactive shock and detonation propagation in U-bend tubes[J].Journal of Prevention in the Process Industries,2007,20(4/5/6):501-508. [14] FROLOV S M,AKSENOV V S,SHAMSHIN I O.Propagation of shock and detonation waves in channels with U-shaped bends of limiting curvature[J].Combustion and Explosion,2008,2(5):759-774. [15] SHINOBU O,MASAYA S,MAKOTO Y.Numerical Investigation on detonation wave through U-bend[J].Journal of Thermal Science,2010,19(6):540-544. [16] QIU Hua,SU Zheng,XIONG Cha.Experimental investigation on multi-cycle two-phase spiral pulse detonation tube of two configurations[J].Journal of Aerospace Engineering,2018,233(11):1-10. [17] 谭汶昊,郑龙席,黄康,等.U型脉冲爆震燃烧室的点火起爆工作特性试验研究[EB/OL].[ 2021-04-08].https:∥doi.org/10.13675/j.cnki.tjjs.200742 [18] BROPHY C M,NETZER D W,SINIBALDI J,et al.Operation of a JP10/air pulse detonation engine[R].Huntsville,Alabama,US:the 36th AlAA/ASME/SAE/ASEE Joint Propulsion Conference,2000. [19] CICCARELLI G,GINSBERG T,BOCCIO J,et al.Detonation cell size measurements and predictions in hydrogen-air-steam mixtures at elevated temperatures[J].Combustion and Flame,1994,99(2):212-220. [20] CICCARELLI G.Flame acceleration in fuel-air mixtures at elevated initial temperatures[R].Indianapolis,Indiana,US:the 38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference,2002. [21] CARD J,CICCARELLI G.DDT in fuel-air mixtures at elevated temperatures and pressures[J].Shock Waves,2005,14(3):167-173. [22] WEN C S,CHUNG K M,LAI W H.Detonation initiation of JP-8-oxygen mixtures at different initial temperatures[J].Shock Waves,2012,22(5):477-482. [23] 李牧.多循环爆震起爆研究[D].西安:西北工业大学,2007. [24] STREHLOW R A.Gas phase detonations:recent developments[J].Combustion and Flame,1968,12(2):81-101. [25] ROY G D,FROLOV S M,BORISOV A A,et al.Pulse detonation propulsion:challenges,current status,and future perspective[J].Progress in Energy and Combustion Science,2004,30(6):549-552. [26] LU Jie,ZHENG Longxi,WANG Zhiwu,et al.Operating characteristics and propagation of back-pressure waves in a multi-tube two-phase valveless air-breathing pulse detonation combustor[J].Experimental Thermal and Science,2015,61:12-23. [27] IBRAHIM I A,FARAG T M,ABDEL-BAKY M E,et al.Experimental study of spray combustion characteristics of air-blast atomizer[J].Energy Reports,2020,6:209-215.
点击查看大图
计量
- 文章访问数: 73
- HTML浏览量: 7
- PDF量: 58
- 被引次数: 0