径向分级低污染燃烧室燃烧性能试验
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摘要
以某型径向三级燃烧室为研究对象,采用天然气为燃料,通过试验研究了各级不同燃料比例及燃烧模式下燃烧室的贫油点火、贫油熄火、出口温度场、污染物排放等燃烧性能。结果表明:在环形区扩散燃烧、主燃区预混燃烧模式下,贫油点火油气比为0.027 0～0.040 1,贫油熄火油气比为0.006 9～0.005 5,环形区改为预混燃烧模式后,点火油气比和熄火油气比均有所增大;随主燃区预混燃料当量比(当量比)的增加,出口温度系数逐步改善,至当量比0.54时则有所恶化,环形区改为预混燃烧模式后,主燃区当量比为0.51时,出口温度系数改善明显;随主燃区当量比的增加,CO、未燃碳氢(UHC)、NO_x及碳烟排放均呈下降趋势,但当量比为0.54时,NO_x排放有所增加,环形区改为预混燃烧模式后,各污染物排放指数降低,但未达到预期。建议径向分级燃烧室在低负荷工况下采用环形区扩散燃烧、主燃区预混燃烧模式,在高负荷工况下均采用预混燃烧方式。
Taking a three-stage radial combustor as the research object and using natural gas as fuel, the combustion performance of lean ignition, lean blowout, outlet temperature field and pollutant emission were experimentally studied under conditions with different fuel ratios and combustion modes. The results show that, in the mode of annular zone diffusion and premixed combustion in the main combustion zone, the fuel-air ratio of lean ignition was 0.027 0～0.040 1, and that of lean blowout was 0.006 9～0.005 5. When the annular zone was changed into premixed combustion mode, both the fuel-air ratio of the ignition and the blowout increased. With an increase in equivalence ratio of the main combustion zone, the outlet temperature coefficient gradually improved, but deteriorated when the equivalence ratio was 0.54. When the equivalent ratio of the main combustion zone was 0.51, the outlet temperature coefficient improved obviously. The mass concentration of CO, unburned hydrocarbon(UHC), NO_x and soot emissions decreased with the increasing equivalence ratio in the main combustion zone, but the NO_x emission increased when the equivalence ratio reached 0.54. When the annular zone was changed to premixed combustion mode, the pollution indexes decreased slightly. It suggests that the combustor should adopt the annular zone diffusion and main combustion zone premixed at lower loads, and the whole premixed combustion mode at higher loads.
Taking a three-stage radial combustor as the research object and using natural gas as fuel, the combustion performance of lean ignition, lean blowout, outlet temperature field and pollutant emission were experimentally studied under conditions with different fuel ratios and combustion modes. The results show that, in the mode of annular zone diffusion and premixed combustion in the main combustion zone, the fuel-air ratio of lean ignition was 0.027 0～0.040 1, and that of lean blowout was 0.006 9～0.005 5. When the annular zone was changed into premixed combustion mode, both the fuel-air ratio of the ignition and the blowout increased. With an increase in equivalence ratio of the main combustion zone, the outlet temperature coefficient gradually improved, but deteriorated when the equivalence ratio was 0.54. When the equivalent ratio of the main combustion zone was 0.51, the outlet temperature coefficient improved obviously. The mass concentration of CO, unburned hydrocarbon(UHC), NO_x and soot emissions decreased with the increasing equivalence ratio in the main combustion zone, but the NO_x emission increased when the equivalence ratio reached 0.54. When the annular zone was changed to premixed combustion mode, the pollution indexes decreased slightly. It suggests that the combustor should adopt the annular zone diffusion and main combustion zone premixed at lower loads, and the whole premixed combustion mode at higher loads.
引文
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[11]程明,尚守堂,刘殿春,等.燃油分级比例对TAPS燃烧室性能的影响[J].航空发动机, 2012, 38(4):6-10.CHENG Ming, SHANG Shoutang, LIU Dianchun, et al.Influence of fuel-staging ratio on TAPS combustor performance[J]. Aero Engine, 2012, 38(4):6-10.
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[13]金如山.航空燃气轮机燃烧室[M].北京:宇航出版社,1988:126-129.JIN Rushan. Combustion chamber of aeronautical gas turbine[M]. Beijing:Astronavigation Press, 1988:126-129.
[14] DINESH K K J R, JENKINS K W, SAVILL A M, et al.Swirl effects on external intermittency in turbulent jets[J]. International Journal of Heat&Fluid Flow, 2012,33(1):193-206.
[15] JOSHI N D, EPSTEIN M J, DURLAK S, et al.Development of a fuel-air premixer for aero-derivative dry low emission combustors[C]. ASME Paper,94-GT-253, 1994.
[16]颜应文,李红红,赵坚行,等.双环预混旋流低污染燃烧室数值研究[J].航空动力学报, 2009, 24(9):1923.YAN Yingwen, LI Honghong, ZHAO Jianxing, et al.Numerical study of low emissions for twin annular premixing swirler combustor[J]. Journal of Aerospace Power, 2009, 24(9):1923.
[17] RESENDE P, AFONSO A, PINHO C, et al. Impacts of dilution on hydrogen combustion characteristics and NOxemissions[C]. ASME Paper, 2017-V008T10A032-71720,2017.
[2] FOUST M, THOMSEN D, STICKLES R, et al.Development of the GE aviation low emissions TAPS combustor for next generation aircraft engines[C]. AIAA Aerospace Sciences Meeting Including the New Horizons Forum&Aerospace Exposition. 2013.
[3] LAZIK W, DOERR T, BAKE S, et al. Development of lean-burn low-NOx combustion technology at Rolls-Royce Deutschland[C]. ASME Turbo Expo 2008:Power for Land, Sea, and Air. Volume 3:Combustion,Fuels and Emissions, Parts A and B Berlin, Germany,June 9-13, 2008.
[4]张宝诚.航空发动机试验和测试技术[M].北京:北京航空航天大学出版社, 2005:338-358.ZHANG Baocheng. Experiment and testing technology of aero-engine[M]. Beijing:Beijing University of Aeronautics and Astronautics Press, 2005:338-358.
[5] KHANNA V. Near-zero NOx gas turbine combustion[C]//Solar Turbine Inc. Proceedings of the 2nd Distributed Energy PeerReview. Washington D. C., USA, Dec. 2-4,2003.
[6]赵坚行.民用发动机污染排放及低污染燃烧技术发展趋势[J].航空动力学报, 2008, 23(6):986.ZHAO Jianxing. Pollutant emission and development of low-emission combustion technology for civil aero engine[J]. Journal of Aerospace Power, 2008, 23(6):986.
[7]刘凯,曾文,刘爱虢.某型燃气轮机燃烧室改进试验[J].热力发电, 2018, 47(8):120-124.LIU Kai, ZENG Wen, LIU Aiguo. Experimental modification for combustor of a gas turbine[J]. Thermal Power Generation, 2018, 47(8):120-124.
[8] FRAZIER T R. Fuel/air mixing and NOx formation in a lean premixed gas turbine combustor[D]. USA:University of Illinois at Urbana-Champaign, 2001:35.
[9]付镇柏,林宇震,傅奇慧,等.不同台阶高度对中心分级燃烧室点火熄火性能的影响[J].航空动力学报,2014, 29(5):1062-1070.FU Zhenbo, LIN Yuzhen, FU Qihui, et al. Effect of different step heights on ignition and blowout performance of internally-staged combustor[J]. Journal of Aerospace Power, 2014, 29(5):1062-1070.
[10]付镇柏,林宇震,张弛,等.中心分级燃烧室进场工况燃油分级方式试验研究[J].推进技术, 2014, 1(1):77.FU Zhenbo, LIN Yuzhen, ZHANG Chi, et al.Experimental investigation on fuel-staging mode of internally-staged combustor under approach condition[J].Journal of Propulsion Technology, 2014, 1(1):77.
[11]程明,尚守堂,刘殿春,等.燃油分级比例对TAPS燃烧室性能的影响[J].航空发动机, 2012, 38(4):6-10.CHENG Ming, SHANG Shoutang, LIU Dianchun, et al.Influence of fuel-staging ratio on TAPS combustor performance[J]. Aero Engine, 2012, 38(4):6-10.
[12] EGGLES R L G, BROWN C T. Comparison of numerical and experimental results of a premixed DLE gas turbine combustor[C]. ASME Paper, 2001-GT-65, 2001.
[13]金如山.航空燃气轮机燃烧室[M].北京:宇航出版社,1988:126-129.JIN Rushan. Combustion chamber of aeronautical gas turbine[M]. Beijing:Astronavigation Press, 1988:126-129.
[14] DINESH K K J R, JENKINS K W, SAVILL A M, et al.Swirl effects on external intermittency in turbulent jets[J]. International Journal of Heat&Fluid Flow, 2012,33(1):193-206.
[15] JOSHI N D, EPSTEIN M J, DURLAK S, et al.Development of a fuel-air premixer for aero-derivative dry low emission combustors[C]. ASME Paper,94-GT-253, 1994.
[16]颜应文,李红红,赵坚行,等.双环预混旋流低污染燃烧室数值研究[J].航空动力学报, 2009, 24(9):1923.YAN Yingwen, LI Honghong, ZHAO Jianxing, et al.Numerical study of low emissions for twin annular premixing swirler combustor[J]. Journal of Aerospace Power, 2009, 24(9):1923.
[17] RESENDE P, AFONSO A, PINHO C, et al. Impacts of dilution on hydrogen combustion characteristics and NOxemissions[C]. ASME Paper, 2017-V008T10A032-71720,2017.