Volume 35 Issue 11
Nov.  2020
Turn off MathJax
Article Contents
LI Xiaofeng, XIAO Junfeng, WANG Wei. Energy distribution characteristics of gas at outlet of ,pulse detonation combustor[J]. Journal of Aerospace Power, 2020, 35(11): 2356-2363. doi: 10.13224/j.cnki.jasp.2020.11.012
Citation: LI Xiaofeng, XIAO Junfeng, WANG Wei. Energy distribution characteristics of gas at outlet of ,pulse detonation combustor[J]. Journal of Aerospace Power, 2020, 35(11): 2356-2363. doi: 10.13224/j.cnki.jasp.2020.11.012

Energy distribution characteristics of gas at outlet of ,pulse detonation combustor

doi: 10.13224/j.cnki.jasp.2020.11.012
  • Received Date: 2020-07-28
  • Publish Date: 2020-11-28
  • In order to improve the energy conversion efficiency of the gas at the outlet of the pulse detonation combustor, a numerical calculation method was used to study the energy distribution characteristics of the gas at the outlet of the pulse detonation combustor with a pneumatic valve and detonation reinforcement structure. Results showed that the expansion process of pulse detonation gas had three stages: primary expansion, secondary expansion and over expansion. The proportion of secondary expansion time and energy was largest in a single cycle; the distribution of gas pressure potential energy, kinetic energy, internal energy and energy flow density at the outlet of the combustion chamber was mainly affected by the gas pressure, and the change law was consistent with the gas pressure; the pressure potential energy, kinetic energy and internal energy of gas increased during the primary expansion stage accounted for 479%, 259% and 251%, respectively, in a single cycle; the pressure potential energy, kinetic energy and internal energy of gas increased during the secondary expansion stage accounted for 502%, 576% and 581%, respectively, in a single cycle.

     

  • loading
  • [1]
    严传俊,范玮.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]
    ANDRUS I Q,KING P I.Evaluation of a high bypass turbofan hybrid utilizing a pulsed detonation combustor[R].AIAA-2007-5074,2007.
    [3]
    CARLOS X,FAKHRE A,OLIVIER P,et al.Analytical model for the performance estimation of pre-cooled pulse detonation turbofan engines[R].ASME Paper GT2017-63776,2017.
    [4]
    GIULIANI F,LANG A,IRANNEZHAD M,et al.Pulse detonation as an option for future innovative gas turbine combustion technologies a concept assessment[R].Nice,France:Congress of the International Council of the Aeronautical Sciences (ICAS),2010.
    [5]
    BELLINI R,LU F K.Exergy analysis of a pulse detonation power device[J].Journal of Propulsion and Power 2010,26(4):875-877.
    [6]
    LU Jie,ZHENG Longxi,QIU Hua,et al.Performance investigation of a pulse detonation turbine engine[J].Journal of Aerospace Engineering,2016,230(2):350-359.
    [7]
    李晓丰,肖俊峰,王玮,等.爆震燃气轮机的变比热容热力循环性能[J].航空动力学报,2016,31(2):369-376. LI Xiaofeng,XIAO Junfeng,WANG Wei,et al.Thermodynamic cycle performance of detonation gas turbine with variable specific heat capacity[J].Journal of Aerospace Power,2016,31(2):369-376.(in Chinese)
    [8]
    李晓丰,肖俊峰,王玮,等.基于爆震燃烧的燃气轮机理想热力循环分析[J].西北工业大学学报,2016,34(1):112-117. LI Xiaofeng,XIAO Junfeng,WANG Wei,et al.Ideal thermodynamic cycle analysis of gas turbine based on detonation combustion[J].Journal of Northwestern Polytechnical University,2016,34(1):112-117.(in Chinese)
    [9]
    邱华,严传俊,范玮.部分充填下脉冲爆震发动机的热力循环性能分析[J].航空动力学报,2008,23(4):718-723. QIU Hua,YAN Chuanjun,FAN Wei.Analysis on thermodynamic performance of partially-fueled pulse detonation engine[J].Journal of Aerospace Power,2008,23(4):718-723.(in Chinese)
    [10]
    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. QIU Hua,YAN Chuanjun,XIONG Cha.A single-cycle performance model of the pulse detonation engine with nozzle[J].Journal of Aerospace Power,2005,20(5):818-821.(in Chinese)
    [11]
    SCHAUER F,BRADLEY R,HOKE J.Interaction of a pulsed detonation engine with a turbine[R].AIAA-2003-0891,2003.
    [12]
    NAGUMO T,SAKURAI T,OBARA T,et al.A study of partial fuel filling for the pulse detonation turbine engine[J].Ryutai Rikigaku Koenkai Koenshu,2005,37(1):325-328.
    [13]
    SHINICHI M,JIRO K,AKIKO M,et al.Analysis on thermal efficiency of non-compressor type pulse detonation turbine engines[J].Transactions of The Japan Society for Aeronautical and Space Sciences,2010,53(181):192-206.
    [14]
    LI Xiaofeng,ZHENG Longxi,QIU Hua,et al.Experimental investigations on the power extraction of a turbine driven by a pulse detonation combustor[J].Chinese Journal of Aeronautics,2013,26(6):1353-1359.
    [15]
    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研究[J].航空动力学报,2013,28(12):2731-2736. LI Xiaofeng,ZHENG Longxi,QIU Hua,et al.Principle experiments on two phase pulse detonation turbine engine[J].Journal of Aerospace Power,2013,28(12):2731-2736.(in Chinese)
    [16]
    LI Xiaofeng,ZHENG Longxi,QIU Hua,et al.The influence of the inlet resistance on the pulse detonation turbine engine[R].Xian:the 4th International Symposium on Jet Propulsion and Power Engineering,2012.
    [17]
    李晓丰,郑龙席,邱华,等.脉冲爆震涡轮发动机原理性试验研究[J].实验流体力学,2013,27(6):1-5. LI Xiaofeng,ZHENG Longxi,QIU Hua,et al.Experimental study on the principle of pulse detonation turbine engine[J].Journal of Experiments in Fluid Mechanics,2013,27(6):1-5.(in Chinese)
  • 加载中

Catalog

    通讯作者: 陈斌, bchen63@163.com
    • 1. 

      沈阳化工大学材料科学与工程学院 沈阳 110142

    1. 本站搜索
    2. 百度学术搜索
    3. 万方数据库搜索
    4. CNKI搜索

    Article Metrics

    Article views (368) PDF downloads(211) Cited by()
    Proportional views
    Related

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return