尾喷管构型对多循环两相脉冲爆轰发动机流场及性能影响
Effects of nozzle on flow field and performance of multi-cycle two-phase pulse detonation engines
-
摘要: 为了研究尾喷管构型对多循环工况下非定常气液两相脉冲爆轰发动机推进性能的影响,运用适应能力强的非结构网格CE/SE(时空守恒元和求解元)方法数值研究了带尾喷管脉冲爆轰发动机的内外流场.结果表明:尾喷管对脉冲爆轰发动机性能的影响在单次循环和多循环工况下有显著差异;当燃料填充率为1、环境压力为0.1MPa时,完成一个周期各种构型尾喷管产生的平均推力由大到小依次为拉伐尔喷管、塞式收敛扩张喷管、收敛喷管、无喷管、直喷管;研究中塞式收敛扩张喷管可以提供最大的冲量和燃料比冲,但完成单个循环的周期最长.Abstract: The CE/SE(conservation element/solution element) method using adaptable unstructured meshes was derived and applied to calculate the inner and outer flow fields of multi-cycle two-phase pulse detonation engines(PDEs) with different types of nozzles.It was found that the propulsive performance of multi-cycle PDEs with nozzles differed a lot from that of one-cycle PDEs with nozzles.The Laval nozzle offered the highest average thrust in a cycle, while the plug-in-convergent-divergent nozzle provided the maximum impulse and fuel-specific impulse in the longest operation cycle when the nozzles were filled with fuel and the ambient pressure was 0.1MPa.
-
[1] Brophy C M,Dausen D F,Smith L R,et al.Fluidic nozzles for pulse detonation combustors [R].AIAA-2012-1035,2012. [2] 范玮,严传俊,李强,等.脉冲爆震发动机尾喷管的实验[J].航空动力学报,2007,22(6):869-872. FAN Wei,YAN Chuanjun,LI Qiang,et al.Experimental investigation on pulse detonation engine nozzles[J].Journal of Aerospace Power,2007,22(6):869-872.(in Chinese) [3] Wang Z W,Yan C J,Fan W,et al.Experimental investigation of the nozzle effects on a two-phase valueless air- breathing pulse detonation engine [R].AIAA-2008-991,2008. [4] 秦亚欣,于军力,高歌.脉冲爆震发动机尾喷管性能数值分析[J].航空动力学报,2010,25(2):366-372. QIN Yaxin,YU Junli,GAO Ge.Computational analysis on the nozzle performance of pulse detonation engines[J].Journal of Aerospace Power,2010,25(2):366-372.(in Chinese) [5] Tsuboi N,Kimura Y,Hayashi A K,et al.Numerical study and performance evaluation for pulse detonation engine with exhaust nozzle [R].AIAA-2009-5315,2009. [6] 黄玥,唐豪,李建中,等.多管脉冲爆震发动机共用尾喷管特性的数值模拟[J].南京航空航天大学学报,2009,41(4):432-438. HUANG Yue,TANG Hao,LI Jianzhong,et al.Numerical investigation on characteristic of multi-tube pulse detonation engines with different common nozzles[J].Journal of Nanjing University of Aeronautics and Astronautics,2009,41(4):432-438.(in Chinese) [7] Kailasanath K.A review of research on pulse detonation engine nozzles [R].AIAA-2001-3932,2001. [8] 曾昊,何立明,章雄伟,等.尾喷管收敛-扩张角对爆震发动机性能影响分析[J].推进技术,2011,32(1):97-102. ZENG Hao,HE Liming,ZHANG Xiongwei,et al.Investigation on the effects of nozzles with different convergent-divergent angle on PDE performance[J].Journal of Propulsion Technology,2011,32(1):97-102.(in Chinese) [9] 李旭东,王春,姜宗林.尾喷管对脉冲爆轰发动机性能的影响[J].力学学报,2011,43(1):1-10. LI Xudong,WANG Chun,JIANG Zonglin.Nozzle effects on performance of pulse detonation engines[J].Chinese Journal of Theoretical and Applied Mechanics,2011,43(1):1-10.(in Chinese) [10] Wu Y,Ma F,Yang V.System performance and thermodynamics cycle analysis of airbreathing pulse detonation engines[J].Journal of Propulsion and Power,2003,19(4):556-567. [11] Chang S C.A new approach for constructing highly stable high order CESE schemes [R].AIAA-2010-543,2010. [12] Cheng G C,Venkatachari B S,Chang C L,et al.Comparative study of different numerical approaches in space-time CESE framework for high-fidelity flow simulations[J].Computers and Fluids,2011,45(1):47-54. [13] 李昕,翁春生.CE/SE方法模拟等离子体电枢二维 MHD 效应[J].工程力学,2009,26(10):240-244. LI Xin,WENG Chunsheng.The 2-D MHD effect of plasma armature simulatied by CE/SE method[J].Engineering Mechanics,2009,26(10):240-244.(in Chinese) [14] Chen Y Y,Yang L,Yu S T J.Simulations of waves in elastic solids of cubic symmetry by the conservation element and solution element method[J].Wave Motion,2011,48(1):39-61. [15] 刘建文,钟诚文,赵书苗.多管脉冲爆震发动机流场数值研究[J].推进技术,2007,28(6):674-678. LIU Jianwen,ZHONG Chengwen,ZHAO Shumiao.Numerical investigation of multi-tube pulse detonation engine[J].Journal of Propulsion Technology,2007,28(6):674-678.(in Chinese) [16] 翁春生,王浩.计算内弹道学[M].北京:国防工业出版社,2006. [17] 马丹花,翁春生.爆震管内扰流片对爆震波影响的数值分析[J].推进技术,2011,32(3):425-430. MA Danhua,WENG Chunsheng.Numerical investigation of two-phase detonation with the obstacles[J].Journal of Propulsion Technology,2011,32(3):425-430.(in Chinese) [18] Wang G,Zhang D,Liu K,et al.An improved CE/SE scheme for numerical simulation of gaseous and two-phase detonations[J].Computers and Fluids,2010,39(1):168-177. [19] Wang X Y,Chang S C.A 2D non-splitting unstructured triangular mesh Euler solver based on the space-time conservation element and solution element method[J].Computational Fluid Dynamics Journal,1999,8(2):309-325. [20] 邱华,严传俊,熊姹,等.脉冲爆震发动机多循环工作过程仿真及性能分析[J].推进技术,2007,28(3):296-301. QIU Hua,YAN Chuanjun,XIONG Cha,et al.Numerical simulation and performance analysis of multi-cycle pulsed detonation rocket engine[J].Journal of Propulsion Technology,2007,28(3):296-301.(in Chinese)
点击查看大图
计量
- 文章访问数: 1352
- HTML浏览量: 3
- PDF量: 1076
- 被引次数: 0