期刊文献+

Experimental investigations on the power extraction of a turbine driven by a pulse detonation combustor 被引量:9

Experimental investigations on the power extraction of a turbine driven by a pulse detonation combustor
原文传递
导出
摘要 In order to grasp the interaction mechanism between the pulse detonation combustor(PDC)and the turbine,the experimental work in this paper investigates the key factors on the power extraction of a turbocharger turbine driven by a PDC.A PDC consisting of an unvalved tube is integrated with a turbocharger turbine which has a nominal mass flow rate of 0.6 kg/s and50000 r/min.The PDC-turbine hybrid engine is operated on gasoline-air mixtures and runs for6+min to achieve a thermal steady state,and then the engine performance is evaluated under different operating conditions.Results show that the momentum difference per unit area between the turbine inlet and outlet plays an important role in the power extraction,while the pressure peak of the detonation has little effect.The equivalence ratio of fuel and air mixture and the transition structure between PDC and turbine are also important to the power extraction of the turbine.The present work is promising as it suggests that the performance beneft of a PDC-turbine hybrid engine can be realized by increasing the momentum difference per unit area through the optimal design of transition section between the PDC and turbine. In order to grasp the interaction mechanism between the pulse detonation combustor(PDC)and the turbine,the experimental work in this paper investigates the key factors on the power extraction of a turbocharger turbine driven by a PDC.A PDC consisting of an unvalved tube is integrated with a turbocharger turbine which has a nominal mass flow rate of 0.6 kg/s and50000 r/min.The PDC-turbine hybrid engine is operated on gasoline-air mixtures and runs for6+min to achieve a thermal steady state,and then the engine performance is evaluated under different operating conditions.Results show that the momentum difference per unit area between the turbine inlet and outlet plays an important role in the power extraction,while the pressure peak of the detonation has little effect.The equivalence ratio of fuel and air mixture and the transition structure between PDC and turbine are also important to the power extraction of the turbine.The present work is promising as it suggests that the performance beneft of a PDC-turbine hybrid engine can be realized by increasing the momentum difference per unit area through the optimal design of transition section between the PDC and turbine.
出处 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2013年第6期1353-1359,共7页 中国航空学报(英文版)
基金 supported by National Natural Science Foundation of China(Grant No.50906072)
关键词 Combustor Experiment Pulse detonation Turbine Turbocharger Combustor Experiment Pulse detonation Turbine Turbocharger
  • 相关文献

参考文献1

二级参考文献13

  • 1Owens Z C, Hanson R K. Unsteady nozzle design for pulse detonation engines. AIAA-2005-3649, 2005.
  • 2Cooper M, Jackson S, Austin J, et al. Direct experimental impulse measurements for detonations and deflagrations. AIAA-2001-3812, 2001.
  • 3Allgood D, Gutmark E, Hoke J, et al. Performance measurements of multi-cycle pulse detonation engine exhaust nozzle. AIAA-2005-222, 2005.
  • 4Wang Z W, Yan C J, Fan W, et al. Experimental investigation of the nozzle effects on a two phase valveless air-breathing pulse detonation engine. AIAA-2008-991, 2008.
  • 5Cambier J L, Tegner J K. Strategies for pulsed detonation engine performance optimization. Journal of Propulsion and Power 1998; 14(4): 489-498.
  • 6Mohanraj R, Merkle C L. A numerical study of pulse detonation engine performance. AIAA-2000-0315, 2000.
  • 7Yungster S. Analysis of nozzle effects on pulse detonation engine performance. AIAA-2003-1316, 2003.
  • 8Wu Y-H, Ma F H, Yang V. System performance and thermodynamic cycle analysis of air-breathing pulse detonation engines. Journal of Propulsion and Power 2003; 19(4): 556-567.
  • 9Tangirala V E, Dean A J. Performance estimations of a pulse detonation engine with exit nozzle. AIAA-2006- 4792, 2006.
  • 10Tsuboi N. Numerical study and peformance evaluation for pulse detonation engine with exhaust nozzle. AIAA-2009-5315, 2009.

共引文献2

同被引文献62

  • 1邱华,严传俊,熊姹.带喷管脉冲爆震发动机单循环性能分析模型[J].航空动力学报,2005,20(5):818-821. 被引量:2
  • 2Suresh A, Hofer D C, Tangirala V E. Turbine Efficiency for Unsteady Periodic Flows[J]. Journal of Turbomachinery, 2012, 134 : 034501.
  • 3Munday D, George A S, Driscoll R, et al. The Design and Validation of a Pulse Detonation Engine Facility with and without Ax- ial Turbine Integration[ R]. AIAA-2013-0275.
  • 4Nicholls J A, Cullen R E, Rag l, et al. Feasibility Studies o f a Rotating Detonation Wave Rocket Motor[J]. Journal of Space- craft, 1996, 3:893-898.
  • 5李晓丰.脉冲爆震涡轮发动机技术研究[D].西安:西北工业大学,2013:102-134.
  • 6KAILASANATH K. Review of propulsion applications of detonation waves[J]. AIAA Journal, 2000, 38(9) : 1698- 1708.
  • 7ROY G D, FROLOV S M, BORISOV A A, et al. Pulse detonation propulsion: Challenges, current status, and fu- ture perspectiveEJ]. Progress in Energy and Combustion Science, 2004, 30(6): 545-672.
  • 8WILLIAM H H, DAVID T P. Thermodynamic cycle analysis of pulse detonation engines[J]. Journal of Propul- sion and Power, 2002, 18(1): 68-76.
  • 9SCRAGG R L. Detonation cycle gas turbine engine system having intermittent fuel and air delivery: US006000214A [P]. 1997-12-14.
  • 10JOHNSON J E, DUNBAR L W, BUTLER L. Combined cycle pulse detonation turbine engine: US6442930BEP]. 2002-09-03.

引证文献9

二级引证文献13

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