燃油喷射方式对凹腔支板稳定器火焰传播性能的影响
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摘要
火焰稳定器的火焰传播性能对燃烧效率与燃烧室长度预测非常重要。在实验验证的基础上,采用三维数值模拟的方法,基于凹腔支板稳定器下游的温度分布及离子浓度分布规律,研究了燃油喷射位置、喷射角度及油气比对凹腔支板稳定器火焰传播性能的影响。研究表明,在来流温度900℃、马赫数0.2、值班油气比4×10-3及主流油气比2.8×10-3~6.8×10-3条件下,支板稳定器下游离子浓度分布趋势与温度分布趋势几乎相同,可同时用来预测火焰传播性能;值班供油位置越靠近稳定器前缘越有利于增强火焰传播性能;当主流油气比为2.8×10-3时,主流喷油位置更靠近稳定器前缘或者采用侧喷方式更有利于火焰传播;随着主流油气比增大至5×10-3~6.8×10-3,主流喷油位置远离稳定器前缘及顺喷方式拥有更加良好的火焰传播性能;喷射角度相同时,喷油位置显著影响油气比对火焰传播性能的影响;喷油位置相同时,改变燃油喷射角度,油气比对火焰传播性能的影响相对较小。
Flame propagation of flameholder is very important for the estimation of combustion efficiency and combustor length. Based on experiments verification,effects of fuel injection position,fuel injection angle and fuel air ratio on the flame propagation of the cavity-based strut flameholder were analyzed by 3D numerical simulation,according to the temperature distribution and ions mole fraction distribution information downstream the flameholder. Under the condition that inlet temperature is 900℃,inlet Ma is 0.2,pilot fuel air ratio is 4×10-3and mainstream fuel air ratio is 2.8×10-3~6.8×10-3,the results show that,the temperature and the ions mole fraction downstream the flameholder have similar distribution,and can be used to analyze the flame propagation simultaneously. It's positive to flame propagation when the pilot fuel injection position is closed to the leading edge of flameholder. In the condition of fuel air ratio being 2.8×10-3,closer mainstream fuel injection position to the leading edge of flameholder or perpendicular injection angle to the main stream is more beneficial to the flame propagation. While with the increasing of fuel air ratio to 5×10-3~6.8×10-3,flame propagation ability increases when the mainstream fuel injection position is away from the leading edge of flameholder or the injection angle is parallel to main stream. In the same fuel injection angle condition,fuel injection position strongly impacts the flame propagation via changing of fuel air ratio. However,in the same fuel injection position,the influence of fuel air ratio on the flame propagation is relatively small with the change of injection angle.
Flame propagation of flameholder is very important for the estimation of combustion efficiency and combustor length. Based on experiments verification,effects of fuel injection position,fuel injection angle and fuel air ratio on the flame propagation of the cavity-based strut flameholder were analyzed by 3D numerical simulation,according to the temperature distribution and ions mole fraction distribution information downstream the flameholder. Under the condition that inlet temperature is 900℃,inlet Ma is 0.2,pilot fuel air ratio is 4×10-3and mainstream fuel air ratio is 2.8×10-3~6.8×10-3,the results show that,the temperature and the ions mole fraction downstream the flameholder have similar distribution,and can be used to analyze the flame propagation simultaneously. It's positive to flame propagation when the pilot fuel injection position is closed to the leading edge of flameholder. In the condition of fuel air ratio being 2.8×10-3,closer mainstream fuel injection position to the leading edge of flameholder or perpendicular injection angle to the main stream is more beneficial to the flame propagation. While with the increasing of fuel air ratio to 5×10-3~6.8×10-3,flame propagation ability increases when the mainstream fuel injection position is away from the leading edge of flameholder or the injection angle is parallel to main stream. In the same fuel injection angle condition,fuel injection position strongly impacts the flame propagation via changing of fuel air ratio. However,in the same fuel injection position,the influence of fuel air ratio on the flame propagation is relatively small with the change of injection angle.
引文
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[16]吴迪,金捷,季鹤鸣,等.凹腔支板尾缘涡脱落频率试验研究[J].航空发动机,2011,37(4):48-51.
[17]吴迪.新型一体化加力燃烧室冷态流场试验研究[D].北京:北京航空航天大学,2010.
[18]刘雯佳,金捷,季鹤鸣.带凹腔支板的数值模拟[J].燃气涡轮试验与研究,2010,(4):35-38.
[19]刘广海,刘玉英.翼型支板火焰稳定器结构参数的研究[J].航空动力学报,2015,30(6):1350-1356.
[20]王伟龙,金捷,井文明,等.改进型一体化加力燃烧室方案的数值模拟[J].航空动力学报,2015,30(5):1119-1124.
[21]罗莲军,刘玉英,张文龙,等.喷油杆与凹腔支板稳定器近距匹配雾化特性[J].航空动力学报,2013,28(11):2462-2467.
[22]罗莲军.凹腔支板稳定器燃烧性能研究[D].北京:北京航空航天大学,2012.
[23]秦伟林,何小民,金义,等.凹腔驻涡与支板稳焰组合加力燃烧室模型冷态流场试验[J].航空动力学报,2012,27(6):1347-1354.
[24]Lovett J A,Ahmed K,Bibik O,et al.On the Influence of Fuel Distribution on the Flame Structure of BluffBody Stabilized Flames[J].Journal of Engineering for Gas Turbines and Power,2014,136(4).
[2]Wright F H,Zukoski E E.Flame Spreading from BluffBody Flameholders[C].Netherlands:Symposium(International)on Combustion,Elsevier,1961.
[3]Thurston D W.An Experimental Investigation of Flame Spreading from Bluff Body Flameholders[D].California:California Institute of Technology,1958.
[4]Hasegawa H,Shimada Y,Kashikawa I,et al.Experimental Study of Compact Ram Combustor with DoubleStaged Flameholders for ATR Engine[C].Salt Lake City:37th Joint Propulsion Conference and Exhibit,2001.
[5]杨茂林,黄勇.燃油分布对V形稳定器后燃烧的影响[J].航空动力学报,1996,11(1):48-52.
[6]Baxter M R,Lefebvre A H,Chin J S.Studies on the Effect of Turbulence on the Spreading Rates of Bluff-Body Stabilized Flames[J].International Journal of Turbo and Jet Engines,1992,9(3):183-190.
[7]韩启祥,王家骅,王维来.测量爆燃到爆震转捩距离的离子探针技术研究[J].航空动力学报,2003,18(1):97-100.
[8]韩启祥,王家骅,王波.预混气爆震管中爆燃到爆震转捩距离的研究[J].推进技术,2003,24(1):63-66.(HAN Qi-xiang,WANG Jia-hua,WANG Bo.Investigation of Deflagration to Detonation Transition Distance in a Tube with Mixture[J].Journal of Propulsion Technology,2003,24(1):63-66.)
[9]徐进生,刘洋,陈先锋,等.甲烷与空气质量浓度当量比对火焰结构及传播特性的影响[J].中国安全科学学报,2014,24(9):64-69.
[10]陈先锋.丙烷-空气预混火焰微观结构及加速传播过程中的动力学研究[D].合肥:中国科学技术大学,2007.
[11]Furukawa J,Hirano T,Williams F A.Burning Velocities of Flamelets in a Turbulent Premixed Flame[J].Combustion and Flame,1998,113(4):487-491.
[12]Roby R J,Hamer A J,Johnson E L,et al.Improved Method for Flame Detection in Combustion Turbines[J].Journal of Engineering for Gas Turbines and Power,1995,117(2):332-340.
[13]Nguyen Q V,Dibble R W,Carter C D,et al.RamanLIF Measurements of Temperature,Major Species,OH,and NO in a Methane-Air Bunsen Flame[J].Combustion and Flame,1996,105(4):499-510.
[14]Ikeda Y,Kojima J,Nakajima T,et al.Measurement of the Local Flamefront Structure of Turbulent Premixed Flames by Local Chemiluminescence[J].Proceedings of the Combustion Institute,2000,28(1):343-350.
[15]吴迪,金捷,季鹤鸣.一种加力燃烧室凹腔支板火焰稳定方案研究[C].贵阳:中国航空学会第七届动力年会论文摘要集,2010.
[16]吴迪,金捷,季鹤鸣,等.凹腔支板尾缘涡脱落频率试验研究[J].航空发动机,2011,37(4):48-51.
[17]吴迪.新型一体化加力燃烧室冷态流场试验研究[D].北京:北京航空航天大学,2010.
[18]刘雯佳,金捷,季鹤鸣.带凹腔支板的数值模拟[J].燃气涡轮试验与研究,2010,(4):35-38.
[19]刘广海,刘玉英.翼型支板火焰稳定器结构参数的研究[J].航空动力学报,2015,30(6):1350-1356.
[20]王伟龙,金捷,井文明,等.改进型一体化加力燃烧室方案的数值模拟[J].航空动力学报,2015,30(5):1119-1124.
[21]罗莲军,刘玉英,张文龙,等.喷油杆与凹腔支板稳定器近距匹配雾化特性[J].航空动力学报,2013,28(11):2462-2467.
[22]罗莲军.凹腔支板稳定器燃烧性能研究[D].北京:北京航空航天大学,2012.
[23]秦伟林,何小民,金义,等.凹腔驻涡与支板稳焰组合加力燃烧室模型冷态流场试验[J].航空动力学报,2012,27(6):1347-1354.
[24]Lovett J A,Ahmed K,Bibik O,et al.On the Influence of Fuel Distribution on the Flame Structure of BluffBody Stabilized Flames[J].Journal of Engineering for Gas Turbines and Power,2014,136(4).