某型燃烧室火焰筒的性能对比试验

黎明; 吴二平; 索建秦; 梁红侠

某型燃烧室火焰筒的性能对比试验

西北工业大学动力与能源学院, 西安 710072

计量
- 文章访问数: 1542
- HTML浏览量: 1
- PDF量: 1190
- 被引次数: 0
出版历程
- 收稿日期: 2013-02-05
- 刊出日期: 2013-08-28

Performance comparative experiment on flame tubes of a certain combustor

School of Power and Energy, Northwestern Polytechnical University, Xi'an 710072, China

摘要

摘要: 为了检验某型航空发动机燃烧室国产化火焰筒的性能,在燃烧室试验台架上,采用连续气源和扇形段试验件,通过模拟燃烧室在最大工况下的工作参数,对该型燃烧室使用的原型火焰筒和国产火焰筒进行了燃烧效率特性、出口温度分布、壁温分布和贫油熄火特性对比试验.试验结果表明:两种火焰筒的燃烧效率特性相同,同一工况下的燃烧效率值接近,相差大约0.5%,国产火焰筒优于原型火焰筒;出口温度场类似,质量指标接近,出口温度分布系数和径向温度分布系数分别相差1%和1.3%,且均在合理范围之内;壁温分布相似,同一位置处最大温差为50K,国产火焰筒高于原型火焰筒;贫油熄火特性一致,在进气速度为150m/s以下,原型火焰筒优于国产火焰筒.
- 航空发动机 /
- 燃烧室 /
- 火焰筒 /
- 燃烧性能 /
- 对比试验
Abstract: In order to examine performance of domestic flame tube for a certain combustor on an active service aero-engine,on the test platform for combustor by means of the continuous air resource and sector rig,comparative experiments of the combustion efficiency characteristic,exit and wall temperature distribution and lean blowout characteristic were conducted to simulate the combustor maximum rating between original and domestic flame tubes. The experimental results show that two kinds of flame tube have the same combustion efficiency characteristic,and the combustion efficiency values are approximate,but the domestic one is 0.5% higher than the original one under identical state.Exit temperature fields are similar,of which indexes of quality are approximate;within reasonable range,the difference of outlet temperature distribution factor is 1% and that of radial temperature distribution factor is 1.3%.Wall temperature distributions are similar;the maximum difference of temperature is 50K on identical position and the domestic one is higher than the original one.Lean blowout characteristics are consistent and the original one is better under 150m/s inlet airflow velocity.
- aero-engine /
- combustor /
- flame tube /
- combustion performance /
- comparative experiment

HTML

参考文献(15)

[1]	侯晓春.高性能航空燃气轮机燃烧技术[M].北京:国防工业出版社,2002.
[2]	林宇震,许全宏,刘高恩.燃气轮机燃烧室[M].北京:国防工业出版社,2008.
[3]	Bahr D W.Technology for the design of high temperature rise combustor.AIAA-85-1292,1985.
[4]	Dodds W J,Bahr D W.Design of modern combustor[M].Salt Lake City,US:Academic Press,1990.
[5]	Kress E J,Taylor J R,Dodds W J.Multiple swirler dome combustor for high temperature rise applications [R].AIAA-90-2159,1990.
[6]	许全宏,林宇震,刘高恩,等.航空发动机高温升燃烧室贫油熄火及冒烟性能研究[J].航空动力学报,2005,20(4):636-640. XU Quanhong,LIN Yuzhen,LIU Gaoen,et al.Research on the high-temperature rise combustor lean blow-out and smoke emission characteristics[J].Journal of Aerospace Power,2005,20(4):636-640.(in Chinese)
[7]	彭云晖,刘旦,林宇震.高温升燃烧室主燃区流场和燃烧性能[J].燃烧科学与技术,2010,16(5):456-461. PENG Yunhui,LIU Dan,LIN Yuzhen.Primary zone flow field and combustion performance of high temperature rise combustor[J].Journal of Combustion Science and Technology,2010,16(5):456-461.(in Chinese)
[8]	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):986-996. ZHAO Jianxing.Pollutant emission and development of low-emission combustion technology for civil aero egine[J].Journal of Aerospace Power,2008,23(6):986-996.(in Chinese)
[9]	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):1923-1929. 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):1923-1929.(in Chinese)
[10]	刘静,肇俊武.国外民用航空发动机低污染燃烧室的发展[J].航空发动机,2012,38(4):11-16. LIU Jing,ZHAO Junwu.Development of low emission combustor for foreign civil aeroengine[J].Aeroengine,2012,38(4):11-16.(in Chinese)
[11]	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.
[12]	甘晓华.航空燃气轮机燃油喷嘴技术[M].北京:国防工业出版社,2006.
[13]	彭泽琰.航空燃气轮机原理[M].北京:国防工业出版社,2000.
[14]	宋双文,蒋荣伟,陈剑,等.离心甩油折流环形燃烧室的性能试验[J].航空动力学报,2007,22(9):1401-1404. SONG Shuangwen,JIANG Rongwei,CHEN Jian,et al.Performance experiment of a reflection flow annular combustor with slinger[J].Journal of Aerospace Power,2007,22(9):1401-1404.(in Chinese)
[15]	杜声同,严传俊.航空燃气轮机燃烧与燃烧室[M].西安:西北工业大学出版社,1995.