反向双旋涡流器受限火焰特性的流场分析
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摘要
分析了反向双旋涡流器受限燃烧火焰特性所对应的流场结构特征.研究发现:反向双旋涡流器流场结构随着受限比变化而发生变化.在受限比小于3.8时,流场上中心回流泡随着受限比增大而变长,与单级旋流涡流器流场上中心回流泡的生长规律相同;但受限比的继续增大,反向双旋涡流器流场上中心回流泡的生长则表现出不同于单级旋流涡流器的规律.单级旋流涡流器流场上中心回流泡会继续生长变长,而反向双旋涡流器流场上中心回流泡会在中间某位置出现分裂,呈现出前后两个不同的回流泡.该研究结果深化了对受限程度影响流动和燃烧的物理机制的认识,同时为反向双旋涡流器的优化设计提供指导.
Flow characteristics of the confined combustion flames of counter dual-stage swirler were analyzed.Research found that,the flow characteristics of the counter dualstage swirler changed with the confinement ratio variation.When the confinement ratio was less than 3.8,the center backflow bubble on this flow field grew longer as the confinement ratio increased,with the growth law the same as that of the center backflow bubble on the single-stage swirler flow field.However,as the confinement ratio continued to increase,the growth law of the center backflow bubble was different between the counter dual-stage swirler and the single-stage swirler.The center backflow bubble on the single-stage swirler flow field continued to grow longer,while the center backflow bubble on the counter dual-stage swirler flow field was split into two different backflow bubbles.This result has deepened the understanding of the effect of confinement on flow and combustion,and provided a guidance for the optimal design of the counter dual-stage swirler.
Flow characteristics of the confined combustion flames of counter dual-stage swirler were analyzed.Research found that,the flow characteristics of the counter dualstage swirler changed with the confinement ratio variation.When the confinement ratio was less than 3.8,the center backflow bubble on this flow field grew longer as the confinement ratio increased,with the growth law the same as that of the center backflow bubble on the single-stage swirler flow field.However,as the confinement ratio continued to increase,the growth law of the center backflow bubble was different between the counter dual-stage swirler and the single-stage swirler.The center backflow bubble on the single-stage swirler flow field continued to grow longer,while the center backflow bubble on the counter dual-stage swirler flow field was split into two different backflow bubbles.This result has deepened the understanding of the effect of confinement on flow and combustion,and provided a guidance for the optimal design of the counter dual-stage swirler.
引文
[1]Tolpadi A K,Burrus D L,Lawson R J.Study of two-phase flow downstream of a gas turbine combustor dome swirl cup[R].ASME Paper 93-GT-392,1993.
[2]Mongia H,Al-Roub,M,Danis A,et al.Swirl cup modelling:PartⅠ[R].AIAA-2001-3576,2001.
[3]Tolpadi A K,Burrus D L,Lawson R J.Numerical computation and validation of two-phase flow downstream of a gas turbine combustor dome swirl cup[J].Journal of Engineering for Gas Turbines and Power,1995,117(4):704-712.
[4]孔文俊,曾青华.一种基于文丘里预混双旋喷嘴的多点直喷燃烧室:中国,CN201210374686[P].2013-01-23.
[5]孔文俊,曾青华.一种基于文丘里预混双旋喷嘴的环形燃烧室:中国,CN201210375557[P].2013-01-23.
[6]Cai J.Aerodynamics of lean direct injection combustor with multi-swirler arrays[D].Ohio:University of Cincinnati,2006.
[7]Fu Y,Jeng S M,Tacina R.Characterics of the swirling flow in a multipoint LDI combustor[R].AIAA-2007-846,2007.
[8]Dewanji D,Rao A G,Pourquie M,et al.Investigation of flow characteristics in lean direct injection combustors[J].Journal of Propulsion and Power,2012,28(1):181-196.
[9]Tacina R R.Low NOx potential of gas turbine engines[R].AIAA 90-0550,1990.
[10]Tacina R,Wey C,Laing P,et al.A low NOx lean-direct injection,multipoint integrated module combustor concept for advanced aircraft gas turbines[R].NASA/TM-2002-211347,2002.
[11]Patel N,Menon S.Simulation of spray-turbulence-flame interactions in a lean direct injection combustor[J].Combustion and Flame,2008,153(1/2):228-257.
[12]曾青华,孔文俊,艾育华,等.贫油直喷三喷嘴模型燃烧室燃烧性能[J].航空动力学报,2014,29(6):1295-1300.ZENG Qinghua,KONG Wenjun,AI Yuhua,et al.Study on combustion performances of lean-direct-injection model combustor with three injectors[J].Journal of Aerospace Power,2014,29(6):1295-1300.(in Chinese)
[13]曾青华,孔文俊,艾育华,等.旋流器结构对贫直喷燃烧室的性能影响[J].航空动力学报,2014,29(8):1775-1781.ZENG Qinghua,KONG Wenjun,AI Yuhua,et al.Effects of swirler structure on the performance of lean-direct-injection combustors[J].Journal of Aerospace Power,2014,29(8):1775-1781.(in Chinese)
[14]ZENG Qinghua,KONG Wenjun,SUI Chunjie.Effect of confinement on combustion characteristics in lean direct injection combustion system[R].ASME Paper GT2013-95413,2013.
[15]Fu Y,Cai J,Jeng S M.et al.Confinement effects on the swirling flow of a counter-rotating swirl cup[R].ASME Paper GT2005-68622,2005.
[16]Fu Y,Jeng S M,Tacina R.Confinement effects on the swirling flow generated by a helical axial swirler[R].AIAA-2006-545,2006.
[2]Mongia H,Al-Roub,M,Danis A,et al.Swirl cup modelling:PartⅠ[R].AIAA-2001-3576,2001.
[3]Tolpadi A K,Burrus D L,Lawson R J.Numerical computation and validation of two-phase flow downstream of a gas turbine combustor dome swirl cup[J].Journal of Engineering for Gas Turbines and Power,1995,117(4):704-712.
[4]孔文俊,曾青华.一种基于文丘里预混双旋喷嘴的多点直喷燃烧室:中国,CN201210374686[P].2013-01-23.
[5]孔文俊,曾青华.一种基于文丘里预混双旋喷嘴的环形燃烧室:中国,CN201210375557[P].2013-01-23.
[6]Cai J.Aerodynamics of lean direct injection combustor with multi-swirler arrays[D].Ohio:University of Cincinnati,2006.
[7]Fu Y,Jeng S M,Tacina R.Characterics of the swirling flow in a multipoint LDI combustor[R].AIAA-2007-846,2007.
[8]Dewanji D,Rao A G,Pourquie M,et al.Investigation of flow characteristics in lean direct injection combustors[J].Journal of Propulsion and Power,2012,28(1):181-196.
[9]Tacina R R.Low NOx potential of gas turbine engines[R].AIAA 90-0550,1990.
[10]Tacina R,Wey C,Laing P,et al.A low NOx lean-direct injection,multipoint integrated module combustor concept for advanced aircraft gas turbines[R].NASA/TM-2002-211347,2002.
[11]Patel N,Menon S.Simulation of spray-turbulence-flame interactions in a lean direct injection combustor[J].Combustion and Flame,2008,153(1/2):228-257.
[12]曾青华,孔文俊,艾育华,等.贫油直喷三喷嘴模型燃烧室燃烧性能[J].航空动力学报,2014,29(6):1295-1300.ZENG Qinghua,KONG Wenjun,AI Yuhua,et al.Study on combustion performances of lean-direct-injection model combustor with three injectors[J].Journal of Aerospace Power,2014,29(6):1295-1300.(in Chinese)
[13]曾青华,孔文俊,艾育华,等.旋流器结构对贫直喷燃烧室的性能影响[J].航空动力学报,2014,29(8):1775-1781.ZENG Qinghua,KONG Wenjun,AI Yuhua,et al.Effects of swirler structure on the performance of lean-direct-injection combustors[J].Journal of Aerospace Power,2014,29(8):1775-1781.(in Chinese)
[14]ZENG Qinghua,KONG Wenjun,SUI Chunjie.Effect of confinement on combustion characteristics in lean direct injection combustion system[R].ASME Paper GT2013-95413,2013.
[15]Fu Y,Cai J,Jeng S M.et al.Confinement effects on the swirling flow of a counter-rotating swirl cup[R].ASME Paper GT2005-68622,2005.
[16]Fu Y,Jeng S M,Tacina R.Confinement effects on the swirling flow generated by a helical axial swirler[R].AIAA-2006-545,2006.
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