斜切径向旋流燃烧室主燃区光学测量与特性分析

陈敏; 宋文艳; 肖隐利; 陈亮; 李建平

斜切径向旋流燃烧室主燃区光学测量与特性分析

西北工业大学动力与能源学院, 西安 710072

基金项目: 西北工业大学基础研究基金(JC20100213)

计量
- 文章访问数: 1724
- HTML浏览量: 9
- PDF量: 1151
- 被引次数: 0
出版历程
- 收稿日期: 2012-08-20
- 刊出日期: 2013-08-28

Optical measurement and characteristic analysis of aeroengine combustor primary zone with counter-rotating swirler

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

摘要

摘要: 针对斜切径向旋流环形燃烧室模型,采用可调谐二极管激光吸收光谱(TDLAS)、相干反斯托克斯喇曼光谱(CARS)光学测量手段,在模化状态(Case 2)下,对燃烧室主燃区进行温度测量,分别得到了主燃区内12个点的温度和沿两条路径的积分温度.使用Fluent 12.0对Case 2进行数值模拟,分别使用两种非预混燃烧模型:平衡化学反应模型(EM)和稳态层流小火焰(SLF)模型.通过将两种不同燃烧模型的计算结果与TDLAS,CARS试验测量数据作对比验证,发现EM计算得到的温度更高,并与试验测量温度更符合,其中与CARS测量的误差小于6%.在试验验证的基础上,完成燃烧室在冷流状态(Case 1)下的计算,分析主燃区的气流组织和主燃孔射流对回流区的影响;利用EM计算分析燃烧室主燃区在全压状态(Case 3)下燃料分布、温度场、组分分布和性能参数,如燃烧室的燃烧效率为0.97、出口温度分布系数为0.312等,较为全面反映了燃烧室内气流流动换热和燃烧现象.
- 可调谐二极管激光吸收光谱(TDLAS) /
- 相干反斯托克斯喇曼光谱(CARS) /
- 平衡化学反应模型 /
- 稳态层流小火焰面模型 /
- 主燃区
Abstract: For an aeroengine annular combustor model,coherent anti-Stokes Raman scattering (CARS) and tunable diode laser absorption spectroscopy (TDLAS) were used to measure temperature in primary zone (PZ) for modeling condition(Case 2).Based on Fluent 12.0 software,two different non-premixed combustion models equilibrium model (EM) and steady laminar flamelet (SLF) model were adopted to calculate the combustor performances for the same case.Then comparison between spectral measured temperature and numerical simulated one shows that higher and more accurate prediction were achieved by EM.What's more,the errors between EM calculation and CARS measurement are less than 6%.For cold flow condition(Case 1),not only detailed analysis of flow field in PZ was made,but also the influence of primary jet on recirculation zone was investigated.Because of the advantage EM was used for full pressure condition (Case 3) to analyze reaction flow field in PZ and calculate combustor performances,including combustion efficiency(0.97),overall temperature distribution factor (OTDF)(0.312),etc.These results indicate reasonable heat transfer and combustion phenomena in combustor model.
- tunable diode laser absorption spectroscopy(TDLAS) /
- coherent anti-Stokes Raman scattering(CARS) /
- chemistry equilibrium model /
- steady laminar flamelet model /
- primary zone

HTML

参考文献(17)

[1]	Reddy A P R,Sujith I,Chakravarthy S R.Swirler flow field characteristics in a sudden expansion combustor geometry using PIV.AIAA 2005-217,2005.
[2]	Brown M S,Barone D L,Terry W F,et al.Accuracy,precision,and scatter in TDLAS measurements [R].AIAA 2010-302,2010.
[3]	Sappey A D,Masterson B P,ZHAO Qingchun,et al.TDLAS measurements of multiple species and temperature of augmented aeroengines [R].AIAA 2009-5064,2009.
[4]	Thariyan M P,Bhuiyan A H,Naik S V.Dual-pump CARS and OH-PLIF measurements at elevated pressures in a gas turbine combustor facility [R].AIAA 2010-4808,2010.
[5]	Mongia H C.Perspective of combustion modeling for gas turbine combustors [R].AIAA Paper 2004-0156,2004.
[6]	Mongia H C.Recent progress in comprehensive modeling of gas turbine combustion [R].AIAA Paper 2008-1445,2008.
[7]	郎洪俭,郭志辉,黄勇.主燃孔对旋流杯下游流场的影响[J].推进技术,2006,27(2):110-113. LANG Hongjian,GUO Zhihui,HUANG Yong.Effect of primary holes on the velocity profiles downstream of a swirl cup[J].Journal of Propulsion Technology,2006,27(2):110-113.(in Chinese)
[8]	党新宪.双旋流环形燃烧室试验研究和数值模拟 [D].南京:南京航空航天大学,2009. DANG Xinxian.Experimental investigation and numerical simulation of a gas turbine annular combustor with dual-stage swirler [D].Nangjing:Nanjing University of Aeronautics and Astronautics,2009.(in Chinese)
[9]	王平,张宝诚.航空发动机燃烧室主燃区的数值模拟分析[J].航空发动机,2005,31(1):47-51. WANG Ping,ZHANG Baocheng.Numerical simulation analysis of an aeroengine combustor primary zone[J].Areoengine,2005,31(1):47-51.(in Chinese)
[10]	Hsiao G,Mongia H C.Swirl cup modeling:Part Ⅲ grid independent solution with different turbulence models [R].AIAA 2003-1349,2003.
[11]	Hsiao G,Mongia H C.Swirl cup modeling:Part Ⅱ inlet boundary conditions [R].AIAA 2003-1350,2003.
[12]	Behrendt T,Hassa C,Mohamed A,et al.In situ measurement and validation of gaseous species concentrations of a gas turbine model combustor by tunable diode laser absorption spectroscopy (TDLAS) [R].Proceedings of ASME Turbo.Expo.,2008.
[13]	解茂昭.内燃机计算燃烧学[M].大连:大连理工大学出版社,2005.
[14]	Lefebvre A H,Ballal D R.Gas turbine combustion[M].Ann Arbor,MI:Edwards Brothers,1999.
[15]	彭泽琰,刘刚.航空燃气轮机原理[M].北京:国防工业出版社,2000.
[16]	焦树建.燃气轮机燃烧室[M].北京:机械工业出版社,1988.
[17]	金如山.航空燃气轮机燃烧室[M].北京:宇航出版社,1985.