Low pollution combustor design and emission performance prediction based on stratified and staged combustion mechanism
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摘要: 保持扩压器尺寸、外机匣最大直径以及燃烧室出口尺寸不变,将燃烧室分别设计为单环腔燃烧室(SAC)、双环腔燃烧室(DAC)、双环预混旋流(TAPS)燃烧室、中心分级燃烧室(CSC)和三旋流燃烧室(TSC)5种燃烧室结构,保持湍流、喷雾、燃烧、辐射及排放数理模型不变,对5种燃烧室进行三维数值模拟.对比研究了5种燃烧室的污染排放性能.结果表明:采用分级燃烧的DAC慢车状态下CO排放量最低,采用DAC在慢车状态下的CO排放量比SAC降低了近62%.采用分层燃烧的TAPS燃烧室的NOx排放量最低,采用TAPS的NOx排放量比SAC降低了近43.5%.Abstract: The dimension of diffuser, maximum diameter of outer casing and dimension of combustor exit were kept the same, and the combustor was designed as single annular combustor(SAC), dual annular combustor(DAC),twin annular premixing swirler(TAPS) combustor,center staged combustor(CSC)and triple-swirler combustor(TSC). The mathematical models(including the turbulence, spray, combustion, radiation and emission) were kept the same, and three-dimensional numerical simulation of five different combustors were developed to compare and study the pollution emission performance of five different combustors. The results show that, the CO emission value of the staged DAC in idle operation is the lowest, and the CO emission value of DAC is 62% lower than that of SAC. NOx emission value of the stratified TAPS combustor in design state is the lowest, and the NOx emission value of TAPS combustor is 43.5% lower than that of SAC.
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[1] 尚守堂,程明,张军峰,等.低排放长寿命燃烧室关键技术分析[R].广东 深圳:中国航空学会2007年学术年会,2007. [2] 航空航天部高效节能发动机文集编委会.高效节能发动机文集:第4分册 燃烧室设计与试验[M].北京:航空工业出版社,1991. [3] 李锋,程明,尚守堂,等.双环预混旋流与单、双环腔燃烧室性能对比[J].航空动力学报,2012,27(8):1681-1688. LI Feng,CHENG Ming,SHANG Shoutang,et al.Capability compare of twin annular premixing swirler with the single annular and dual annular combustor[J].Journal of Aerospace Power,2012,27(8):1681-1688.(in chinese) [4] Mongia H C.TAPS:a 4th generation propulsion combustor technology for low emissions[R].AIAA-2003-2657,2003. [5] Mongia H C.Swirl cup modeling:Part Ⅱ inlet boundary conditions[R].AIAA-2003-1350,2003. [6] McKinney R G.The Pratt &Whitney TALON X low emissions combustor:revolutionary results with evolutionary technology[R].AIAA-2007-386,2007. [7] Mongia H C.Recent progress in comprehensive modeling of gas turbine combustion[R].AIAA-2008-1445,2008. [8] Rizk N K,Mongia H C.Three-dimensional NOx modeling for rich/lean combustor[R].AIAA 93-0251,1993. [9] Maier G,Wittig S.Fuel preparation and emission character of a pressure loaded LPP combustor[R].AIAA 99-3774,1999. [10] Michou Y,Chauvear C,Gokalp I.Experimental study of lean premixed and prevaporised turbulent spray combustion[R].AIAA 99-0332,1999. [11] Micklow G J,Roychoudhury S,Nguyen H L,et al.Emission reduction by varying the swirler air flow split in advanced gas turbine combustors[R].ASME Paper 92-GT-110,1992. [12] Zarzalis N,Joos F,Glaeser B.NOx-reduction by rich-lean combustion[R].AIAA 92-3339,1992. [13] Colantonio R O.The applicability of jet-shear-layer mixing and effervescent atomization for low-NOx combustors[J].Journal of Engineering for Gas Turbines and Power,1998,120(1):17-23. [14] Bahr D W,Gleason C C.Experimental clean combustor program:Phase Ⅰ final report[R].NASA CR-134732,1975. [15] Li G,Gutmark E J,Stankovic D.Experimental study of flameless combustion in gas turbine combustor[R].AIAA 2006-546,2006. [16] Flamme M.New combustion systems for gas turbines (NGT)[J].Applied Thermal Engineering,2004,24(11/12):1551-1559. [17] Levy Y,Sherbaum V,Arfi P.Basic thermodynamics of FLOXCOM:the low-NOx gas turbines adiabatic combustor[J].Applied Thermal Engineering,2004,24(11/12):1593-1605. [18] Dhanuka S K.Unsteady aspects of lean premixed prevaporized (LPP) gas turbine combustors:flame-flame interaction[R].AIAA-2010-1148,2010. [19] Dhanuka S K.Vortex-shedding and mixing layer effects on periodic flashback in a lean premixed prevaporized gas turbine combustor[R].AIAA-2011-1243,2011. [20] Dhanuka S K.Instantaneous flow structures in a reacting gas turbine combustor[R].AIAA-2008-4683,2008. [21] 李锋,尚守堂,程明,等.双环腔燃烧室置换单环腔燃烧室可行性研究[J].航空动力学报,2008,23(1):145-149. LI Feng,SHANG Shoutang,CHENG Ming,et al.Research on the feasibility of displacing the single annular combustor with a dual annular combustor[J].Journal of Aerospace Power,2008,23(1):145-149.(in Chinese)
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