Volume 35 Issue 6
Jun.  2020
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LIU Aiguo, LI Yuze, YANG Yudong. Experiment on combustion characteristics of micro gas turbine combustor[J]. Journal of Aerospace Power, 2020, 35(6): 1335-1344. doi: 10.13224/j.cnki.jasp.2020.06.024
Citation: LIU Aiguo, LI Yuze, YANG Yudong. Experiment on combustion characteristics of micro gas turbine combustor[J]. Journal of Aerospace Power, 2020, 35(6): 1335-1344. doi: 10.13224/j.cnki.jasp.2020.06.024
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Experiment on combustion characteristics of micro gas turbine combustor

doi: 10.13224/j.cnki.jasp.2020.06.024

  • Liaoning Key Laboratory of Advanced Measurement and Test Technology for,Aviation Propulsion System,School of Aero-Engine,Shenyang Aerospace University,Liaoning Shenyang 110136,China

  • Received Date: 2019-12-02
  • Publish Date: 2020-06-28
    Abstract
  • According to the requirements of low pollution emission of gas turbine, the combustion characteristic experiment was carried out on the single head experiment piece of the combustor of low emission micro gas turbine designed for the use of gas fuel. The position and quantity of the fuel nozzle, the fuel distribution ratio between the duty class and the main combustion stage, and the combustion efficiency and pollutant emission characteristics under different air flow distribution modes were compared and analyzed. Results showed that changing the position and quantity of the fuel nozzle can change the mixing characteristics of the fuel and air, yielding a great effect on the combustion characteristics; the change of the fuel flow distribution ratio between the duty class and the main combustion stage led to the change of the equivalence ratio of each combustion zone, and the reduction of the current ratio of the main combustion stage to below 08 was conducive to the reduction of pollutant emissions; the change of air flow distribution ratio of the combustion chamber was conducive to the reduction of pollutant emissions With this method, the equivalence ratio of the main combustion zone can be reduced, the NOx emission can be reduced to 272 mg/m3, and the combustion efficiency can reach 986%. However, the decrease of air flow rate for mixing could increase the outlet temperature distribution coefficient from 021 to 024.

     

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    • References(22)
  • [1]
    赵岩.天然气贫预混燃烧器燃空掺混与燃烧特性研究［D］.北京:中国科学院,2016. ZHAO Yan.Investigation of fuel/air mixing and combustion characteristics of a lean premixed burner for natural gas turbine application［D］.Beijing:Chinese Academy of Sciences,2016.(in Chinese)
    [2]
    孙宝成.燃气轮机燃料/空气掺混规律的数值研究［D］.北京:清华大学,2007. SUN Baocheng.Numerical study of fuel/air unmixedness in a nonreacting gas turbine combustor［D］.Beijing:Tsinghua University,2007.(in Chinese)
    [3]
    李娜,张强,邵思东,等.重型车用稀燃天然气发动机碳氢排放特性［J］.农业工程学报,2013,29(2):45-51. LI Na,ZHANG qiang,SHAO Sidong,et al.HC emission characteristics of heavy vehicle equipped with lean-burn natural gas engine［J］.Transactions of the Chinese Society of Agricultural Engineering,2013,29(2):45-51.(in Chinese)
    [4]
    冯冲,祁海鹰,谢刚,等.R0110燃烧室预混均匀性与排放的研究［J］.工程热物理学报,2010,31(8):1431-1434. FENG Chong,QI Haiying,XIE Gang,et al.Study on premixing uniformity and emission of R0110 combustor［J］.Journal of Engineering Thermophysics,2010,31(8):1431-1434.(in Chinese)
    [5]
    李宇红,孙宝成,祁海鹰.燃烧室预混段燃料/空气混合规律的数值研究［J］.热能动力工程,2008,23(3):235-239. LI Yuhong,SUN Baocheng,QI Haiying.A numerical study of the fuel/air mixing law specific to the premixing section of a gas turbine combustor［J］.Journal of Engineering for Thermal Energy and Power,2008,23(3):235-239.(in Chinese)
    [6]
    李孟涵,张强,李国祥,等.引燃柴油量及喷射间隔对直喷天然气发动机排放的影响［J］.农业工程学报,2016,32(6):95-100. LI Menghan,ZHANG Qiang,LI Guoxiang,et al.Effects of diesel injection quantity and injection interval on emission characteristics of directly injected natural gas engine［J］.Transactions of the Chinese Society of Agricultural Engineering,,2016,32(6):95-100.(in Chinese)
    [7]
    谢刚,李宇红,祁海鹰.DLN燃烧室的燃料-空气预混均匀性研究［J］.工程热物理学报,2006,27(增刊2):227-230. XIE Gang,LI Yuhong,QI Haiying.Experimental study on non-uniformity off fuel/air premixing in a DLN combustor［J］.Journal of Engineering Thermophysics,2006,27(Suppl.2):227-230.(in Chinese)
    [8]
    康振亚,郑洪涛,贾翔羽,等.微型燃气轮机燃烧室预混结构性能研究及改进［J］.燃气轮机技术,2013,26(1):21-26. KANG Zhenya,ZHENG Hongtao,JIA Xiangyu,et al.Research and improvement of performance of micro-turbine combustor premixing structure［J］.Gas Turbine Technology,2013,26(1):21-26.(in Chinese)
    [9]
    刘凯,张宝诚,马洪安.过量空气系数对DLN燃烧室性能影响的基本规律［J］.热力发电,2010,39(8):8-11. LIU Kai,ZHANG Baocheng,MA Honfan.Basic influence regularity of excess air coefficient upon the performance of DLN combuster［J］.Thermal Power Generation,2010,39(8):8-11.(in Chinese)
    [10]
    邢畅,邱朋华,刘栗,等.燃料预混特性对燃烧室燃烧特性的影响［J］.推进技术,2016,37(11):2114-2119. XING Chang,QIU Penghua,LIU Li,et al.Effects of fuel premixed characteristics on combustion characteristics of combustor［J］.Journal of Propulsion Technology,2016,37(11):2114-2119.(in Chinese)
    [11]
    祝俊宗,胡羽,夏单城,等.改善低NOx燃烧室预混均匀性的结构优化策略［J］.中国电机工程学报,2017,37(21):6353-6362. ZHU Junzong,HU Yu,XIA Dancheng,et al.Structural optimization strategy of improving the premixing uniformity in a low NOx combustor［J］.Proceedings of the CSEE,2017,37(21):6353-6362.(in Chinese)
    [12]
    ADZIC M,FOTEV V,MILIVOJEVIC A,et al.Effect of a microturbine combustor type on emissions at lean-premixed conditions［J］.Journal of Propulsion and Power,2010,26(5):1135-1143.
    [13]
    FURUHATA T,AMANO S,YOTORIYAMA K,et al.Development of can-type low NOx combustor for micro gas turbine(fundamental characteristics in a primary combustion zone with upward swirl)［J］.Fuel,2007,86(15):2463-2474.
    [14]
    薛鑫,林宇震,张弛,等.火焰筒压力损失对贫油熄火特性和燃烧效率的影响［J］.航空动力学报,2012,27(12):2687-2691. XUE Xin,LIN Yuzhen,ZHANG Chi,et al.Effects of liner pressure loss on combustor lean blow-out and combustion efficienly performances［J］.Journal of Aerospace Power,2012,27(12):2687-2691.(in Chinese)
    [15]
    汪凤山.低 NOx排放微型燃气轮机燃烧室的数值模拟及实验研究［D］.北京:中国科学院,2009. WANG Fengshan.Numerical simulation and experimental study on combustion chamber of micro gas turbine with low NOx emission［D］.Beijing:Chinese Academy of Sciences,2009.(in Chinese)
    [16]
    付忠广,张译中,卢可,等.合成气微型燃气轮机旋流燃烧特性数值模拟［J］.热力发电,2015,44(3):15-20. FU Zhongguang,ZHANG Yizhong,LU Ke,et al.Numerical study on swirl combustion characteristics of micro gas turbine combustor burning syngas［J］.Thermal Power Generation,2015,44(3):15-20.(in Chinese)
    [17]
    邢畅,邱朋华,刘栗,等.起动机驱动过程中微型燃气轮机燃烧室变工况燃烧特性［J］.中国电机工程学报,2018,38(8):2367-2375. XING Chang,QIU Penghua,LIU Li,et al.Off-design combustion performance under starter-driven process for a micro-gas turbine combustor［J］.Proceedings of the CSEE,2018,38(8):2367-2375.(in Chinese)
    [18]
    刘爱虢,陈思,李昱泽,等.微型燃气轮机燃烧室性能实验测试［J］.热力发电,2019,48(6):71-78. LIU Aiguo,CHEN Si,LI Yuze,et al.Combustion characteristics test for a micro-gas turbine combustor［J］.Thermal Power Generation,2019,48(6):71-78.(in Chinese)
    [19]
    REN Z,YANG H,LU T.Effects of small-scale turbulence on NOx formation in premixed flame fronts［J］.Fuel,2014,115(1):241-247.
    [20]
    林宇震,林阳,张弛,等.先进燃烧室分级燃烧空气流量分配的探讨［J］.航空动力学报,2010,25(9):1923-1930. LIN Yuzhen,LIN Yang,ZHANG Chi,et al.Discussion on combustion airflow distribution of advanced staged combustor［J］.Journal of Aerospace Power,2010,25(9):1923-1930.(in Chinese)
    [21]
    秦皓,汤冠琼,林宇震,等.燃油分级比对LESS燃烧室压力振荡频率的影响.［J］.航空动力学报,2015,30(6):1337-1343. QIN Hao,TANG Guanqiong,LIN Yuzhen,et al.Influence of fuel stage ratio on pressure oscillation frequency of LESS combustor［J］.Journal of Aerospace Power,2015,30(6):1337-1343.(in Chinese)
    [22]
    金如山,索建秦.先进燃气轮机燃烧室［M］.北京:航空工业出版社,2016.(编辑：叶青、王碧珺)
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