Volume 30 Issue 6
Jun.  2015
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LIU Qian, ZHENG Hong-tao, LI Zhi-ming, CHEN Xi. Performance of continuously rotating detonation combustor[J]. Journal of Aerospace Power, 2015, 30(6): 1328-1336. doi: 10.13224/j.cnki.jasp.2015.06.006
Citation: LIU Qian, ZHENG Hong-tao, LI Zhi-ming, CHEN Xi. Performance of continuously rotating detonation combustor[J]. Journal of Aerospace Power, 2015, 30(6): 1328-1336. doi: 10.13224/j.cnki.jasp.2015.06.006

Performance of continuously rotating detonation combustor

doi: 10.13224/j.cnki.jasp.2015.06.006
  • Received Date: 2014-01-23
  • Publish Date: 2015-06-28
  • Using two-dimensional compressible Euler equations, the flow field in continuously rotating detonation combustor (CRDC) with equivalent hydrogen/air was numerically analyzed. The effects of fuel inflow total pressure at different azimuthal sizes of CRDC on pressure ratio, combustion efficiency, volume heat release rate and NOx emissions were examined. The results show that with the increase of fuel inflow total pressure, when azimuthal size of CRDC is 150mm, pressure ratio remains unchanged, and combustion efficiency and volume heat release rate grow linearly; when azimuthal size of CRDC is 250mm, detonation wave number redoubles, and volume heat release rate still grow linearly, but pressure ratio and combustion efficiency turn down due to the increase of fuel inflow total pressure. Compared with conventional isobaric combustor, CRDC has a higher performance. In the calculation region of 250mm×40mm, the pressure ratio goes up to 2.706, greatly improving the potential power of gas; volume heat release rate is 2.18 ×1010W/m3; NOx emissions is 0.692mg/m3, thereby ensuring low emissions requirements.

     

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  • [1]
    李孝堂,梁春华.世界航改舰船用燃气轮机的发展趋势[J].航空科学技术,2011(6):4-7. LI Xiaotang,LIANG Chunhua.Development trend of world aero-derivative marine gas turbines[J].Aeronautical Science and Technology,2011(6):4-7.(in Chinese)
    [2]
    Wolanski P.Detonative propulsion[J].Proceedings of the Combustion Institute,2013,34(1):125-158.
    [3]
    邵业涛,刘勐,王健平.圆柱坐标系下连续旋转爆轰发动机的数值模拟[J].推进技术,2009,30(6):717-721. SHAO Yetao,LIU Meng,WANG Jianping.Numerical simulation of continuous rotating detonation engine in column coordinate[J].Journal of Propulsion Technology,2009,30(6):717-721.(in Chinese)
    [4]
    邵业涛,王健平.连续爆轰发动机的二维数值模拟研究[J].航空动力学报,2009,24(5):980-986. SHAO Yetao,WANG Jianping.Two dimensional simulation of continuous detonation engine[J].Journal of Aerospace Power,2009,24(5):980-986.(in Chinese)
    [5]
    唐新猛,王健平,邵业涛.连续旋转爆轰波在无内柱圆筒内的数值模拟[J].航空动力学报,2013,28(4):792-799. TANG Xinmeng,WANG Jianping,SHAO Yetao.3-D simulation of rotating detonation wave in combustion chambers without inner wall[J].Journal of Aerospace Power,2013,28(4):792-799.(in Chinese)
    [6]
    ZHOU Rui,WANG Jianping.Numerical investigation of flow particle paths and thermodynamic performance of continuously rotating detonation engines[J].Combustion and Flame,2012,159(12):3632-3645.
    [7]
    Schwer D,Kailasanath K.Fluid dynamics of rotating detonation engines with hydrogen and hydrocarbon fuels[J].Proceedings of the Combustion Institute,2013,34(2):1991-1998.
    [8]
    Yamada T,Hayashi A K,Yamada E,et al.Detonation limit thresholds in H2/O2 rotating detonation engine[J].Combustion Science and Technology,2010,182(11/12):1901-1914.
    [9]
    Bykovskii F A,Zhdan S A,Vedernikov E F.Continuous spin detonation in annular combustors[J].Combustion,Explosion,and Shock Waves,2005,41(4):449-459.
    [10]
    Bykovskii F A,Zhdan S A,Vedernikov E F.Continuous spin detonation of hydrogen-oxygen mixtures:2 combustor with an expanding annular channel[J].Combustion,Explosion,and Shock Waves,2008,44(3):330-342.
    [11]
    SHAO Yetao,LIU Meng,WANG Jianping.Numerical investigation of rotating detonation engine propulsive performance[J].Combustion Science and Technology,2010,182(11/12):1586-1597.
    [12]
    SHAO Yetao,LIU Meng,WANG Jianping.Continuous detonation engine and effects of different types of nozzle on its propulsion performance[J].Chinese Journal of Aeronautics,2010,23(6):647-652.
    [13]
    Schwer D,Kailasanath K.Numerical investigation of the physics of rotating-detonation-engines[J].Proceedings of the Combustion Institute,2011,33(2):2195-2202.
    [14]
    Davidenko D M,Gökalp I.Numerical study of the continuous detonation wave rocket engine[R].AIAA-2008-2680,2008.
    [15]
    Davidenko D M,Jouot F,Kudryavtsev A N,et al.Continuous detonation wave engine studies for space application[J].Progress in Propulsion Physics,2009,1:353-366.
    [16]
    Bykovskii F A,Zhdan S A,Vedernikov E F.Continuous spin detonation of hydrogen-oxygen mixtures:1 annular cylindrical combustors[J].Combustion,Explosion,and Shock Waves,2008,44(2):150-162.
    [17]
    马虎,武晓松,王栋,等.旋转爆震发动机数值研究[J].推进技术,2012,33(5):820-825. MA Hu,WU Xiaosong,WANG Dong,et al.Numerical investigation for rotating detonation engine[J].Journal of Propulsion Technology,2012,33(5):820-825.(in Chinese)
    [18]
    Hishida M,Fujiwara T,Wolanski P.Fundamentals of rotating detonations[J].Shock Waves,2009,19(1):1-10.
    [19]
    Bykovskii F A,Vedernikov E F.Continuous detonation of a subsonic flow of a propellant[J].Combustion,Explosion and Shock Waves,2003,39(3):323-334.
    [20]
    包文飞,李明,牟影,等.R0110重型燃气轮机DLN燃烧室NOx排放特性研究[J].燃气涡轮试验与研究,2013,26(1):40-42. BAO Wenfei,LI Ming,MOU Ying,et al.NOx emissions properties of DLN combustor of R0110 heavy duty gas turbine[J].Gas Turbine Experiment ans Research,2013,26(1):40-42.(in Chinese)
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