一种离心喷嘴多孔蒸发管的蒸发率实验

光辉; 许全宏; 朱菁; 林宇震

一种离心喷嘴多孔蒸发管的蒸发率实验

北京航空航天大学能源与动力工程学院航空发动机气动热力国家级重点实验室,北京 100191

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出版历程
- 收稿日期: 2009-08-27
- 修回日期: 2010-12-20
- 刊出日期: 2011-02-28

Experimental study of evaporation rate for multihole vaporizer with pressure swirl atomizer

National Key Laboratoryof Science and Technology on Aero-Engine Aero-thermodynamics, School of Jet Propulsion,Beijing University of Aeronautics and Astronautics, Beijing 100191,China

摘要

摘要: 发展了一种用于微小型燃气轮机燃烧室的多孔蒸发管,燃油通过离心喷嘴供入蒸发管上游,空气经喷嘴下游的多个离散小孔进入蒸发管,燃油在蒸发管内与空气混合并蒸发.测试了离心喷嘴的喷雾特性,并主要对该多孔蒸发管的燃油蒸发率进行了实验.结果表明:对于这种多孔蒸发管,影响蒸发率的主要因素是进气温度和离心喷嘴的喷雾特性,当进气温度超过480K,煤油接近完全蒸发,雾化颗粒度越小,相对流速越大,蒸发完全程度越高.
- 蒸发管 /
- 多孔 /
- 离心喷嘴 /
- 蒸发率 /
- 燃烧室
Abstract: A design multihole vaporizer was developed for micro gas turbine combustor.Pressure swirl atomizer was used to atomize kerosene first and was fitted at entrance of multihole vaporizer.A lap of holes were distributed around multihole vaporizer wall of nozzle downstream,which were used to mix and vaporize kerosene.Spray characteristics of pressure swirl atomizer was measured,and vaporization rate of the multihole vaporizer was studied experimentally.The experimental results show that the air temperature and spray characteristics of pressure swirl atomizer are major influence factor to vaporization rate for multihole vaporizer.Kerosene is completely vaporized when the vaporizer inlet temperature exceeds 480K.The smaller the kerosene particle size,the greater relative velocity,the higher the level of evaporation achieved.
- vaporizer /
- multihole /
- pressure swirl atomizer /
- vaporization rate /
- combustor

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参考文献(12)

[1]	Lefebvre A H.Gas turbine combustion[M].Philadelphia,USA:Taylor & Francis,1999.
[2]	Dbbeling K,Hellat J,Koch H.25 years of bbc/abb/alstom lean premix combustion technologies .ASME Paper 2005-GT-68269,2005.
[3]	Colibaba-Evulet A,Bowman M J,Brand A R.Design and evaluation of the aims combustor .ASME Paper 2004-GT-53150,2004.
[4]	Nakamura S,McDonell V,Samuelsen S.The effect of liquid-fuel preparation on gas turbine emissions .ASME Paper 2006-GT-90730,2006.
[5]	Lee J C Y,Malte P C,Benjamin M A.Low nox combustion for liquid fuels:atmospheric pressure experiments using a staged prevaporizer-premixer .ASME Paper 2001-GT-0081,2001.
[6]	林宇震,彭云晖,刘高恩.分级/预混合预蒸发贫油燃烧低污染方案NO_x排放初步研究[J].航空动力学报,2003,18(4):492-497. LIN Yuzhen,PENG Yunhui,LIU Gaoen.A preliminary study of nox emission of staging/premixed and prevaporized lean combustion low emission combustor scheme[J].Journal of Aerospace Power,2003,18(4):492-497.(in Chinese)
[7]	LIN Yuzhen,PENG Yunhui,LIU Gaoen.Investigation on nox of a low emission combustor design with multihole premixer-prevaporizer .ASME Paper 2004-GT-53203,2004.
[8]	Gokulakrishnan P,Gaines G,Klassen M S,et al.Autoignition of aviation fuels:experimental and modeling study .AIAA 2007-5701.2007.
[9]	朱菁.微型燃气轮机液体燃料低污染燃烧基础研究 .北京:北京航空航天大,2007. ZHU Jing.Fundamental investigation of low emission combustion technology used liquid fuel for microturbine-generator .Beijing:Bejing University of Aeronautics and Astronautics,2007.(in Chinese)
[10]	Suzuki T K,Oppata Y.A study of a fuel vaporizer for a gas turbine engine .Tokyo,Japan:Tokyo Joint International Gas Turbine Conference and Product Show,1971:135-142.
[11]	朱菁,郭新华,林宇震,等.微小“T”型蒸发管蒸发率实验[J].航空动力学报,2007,22(8):1274-1278. ZHU Jing,GUO Xinhua,LIN Yuzhen,et al.Experimental research on vaporization rate of micro “T”-vaporizer[J].Journal of Aerospace Power,2007,22(8):1274-1278.(in Chinese)
[12]	金如山.航空燃气轮机燃烧室[M],北京:宇航出版社,1985. JIN Rushan.Aviation gas turbine combustor[M].Beijing: China Astronautics Publishing House,1985.(in Chinese)