期刊文献+

障碍物对脉冲爆震发动机性能影响的数值模拟 被引量:1

Numerical Simulation of Effect of Obstacles on Pulse Detonation Engine Performances
原文传递
导出
摘要 运用计算流体力学方法计算了理想脉冲爆震发动机(PDE)单次爆震的性能参数,并和Wintenberger半分析模型进行了对比,研究了圆环形障碍物阻塞比和节距内径比对空气流动损失和脉冲爆震发动机单次爆震性能的影响,并与连续的多脉冲爆震实验的相关结果做了比较。研究结果表明,数值模拟计算得到的冲量和Wintenberger半分析模型得到的冲量非常接近,佐证了数值模拟方法和结果的正确性;障碍物阻塞比增大、节距内径比减小或进口速度增大,空气流过障碍物时的总压恢复系数减小,流动损失增大;障碍物阻塞比增大,单次爆震的体积比冲减小,单位燃油消耗率增大,性能降低;当阻塞比为41%时,体积比冲为理想爆震管体积比冲的92%,损失了8%;障碍物节距内径比增大,单次爆震的体积比冲先减小后增大,而单位燃油消耗率先增大后减小,不同节距内径比的体积比冲为理想爆震管体积比冲的94%左右,不同节距内径比对性能影响规律与多次脉冲爆震实验结果趋势符合。 The performance parameters of the single-cycle detonation wave of an ideal pulse detonation engine (PDE) are calculated by solving unsteady two-dimensional (2D) reacting N-S equations, and these parameters are compared with the results obtained from the Wintenberger semi analytic model. The effects of ring obsta- cles on the loss of air flowing through the PDE and the performances of single-cycle detonation wave of the PDE are studied. The data of numerical simulation are compared with those of multi-pulse detonation experi- ments conducted on a 60 mm inner diameter detonation tube. The results show that the calculated impulse is almost the same as the impulse used by the Wintenberger semi-analytic model, which means the numerical sim- ulation method is valid. The blockage ratio increases, or the obstacle pitch and inner diameter ratio decreases, while the total pressure recovery coefficient decreases. The blockage ratio increases, the impulse per unit vol- ume of single-cycle detonation wave decreases and the specific fuel consumption increases. When the blockage ratio is about 41%, the impulse per unit volume is 92 % of that of the ideal PDE. The obstacle pitch and inner diame- ter ratio increases, the impulse per unit volume of single-cycle detonation wave first decreases and then increases, while the specific fuel consumption first increases and then decreases. This effect of different obstacle pitch and inner diameter ratios on PDE performance agrees with that of the multi-pulse detonation experiments.
出处 《航空学报》 EI CAS CSCD 北大核心 2009年第4期614-621,共8页 Acta Aeronautica et Astronautica Sinica
基金 国家自然科学基金(50336030)
关键词 脉冲爆震发动机 障碍物 单次爆震 数值模拟 模型 pulse detonation engine obstacle single-cycle detonation wave numerical simulation models
  • 相关文献

参考文献5

  • 1Shchelkin K I. Combustion and detonation in gases[M]. Moscow: Voenizdat, 1944. (in Russian)
  • 2Cooper M, Jackson S, Austin J. Direct experimental impulse measurements for detonations and deflagrations[R]. AIAA- 2001- 3812, 2001.
  • 3杜魁善.脉冲爆震发动机原理样机设计与性能分析[D].西安:西北工业大学,2004.
  • 4李牧,严传俊,王治武,邱华,郑龙席.障碍物强化爆震起爆和传播的数值模拟与验证[J].西北工业大学学报,2006,24(3):299-303. 被引量:7
  • 5Wintenberger E, Austin J, Cooper M. Analytical model for the impulse of single-cycle pulse detonation tube[J]. Jour nal of Propulsion and Power, 2003, 19(1): 22-38.

二级参考文献6

  • 1Kailasanath K. Recent Developments in the Research on Pulse Detonation Engines. AIAA Journal, 2003, 41(2):145-149
  • 2Roy G D, Frolov S M, Borisov A A, et al. Pulse Detonation Propulsion: Challenges, Current Status, and Future Perspective. Progress in Energy and Combustion Science, 2004, 30: 546- 549
  • 3Tangirala V E, Varatharajan B, Dean A J. Numerical Investigations of Detonation Initiation. AIAA 2003-0716
  • 4Ma Fuhua, Choi Jeongyeol, Yang Vigor. Thrust Chamber Dynamics and Propulsive Performance of Single-Tube Pulse Detonation Engines. AIAA 2004-0865
  • 5Im Kyoungsu, Yu S T John. Analyses of Direct Detonation Initiation with Realistic Finite-Rate Chemistry. AIAA 2003-1318
  • 6Harris P G, Farinacio R, Stowe R A, et al. The Effect of DDT Distance on Impulse in a Detonation Tube. AIAA 2001-3467

共引文献6

同被引文献3

引证文献1

二级引证文献4

相关作者

内容加载中请稍等...

相关机构

内容加载中请稍等...

相关主题

内容加载中请稍等...

浏览历史

内容加载中请稍等...
;
使用帮助 返回顶部