小型回流燃烧室燃烧特性数值研究
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摘要
某科研样机采用蒸发管回流燃烧室,其燃烧室结构复杂,燃烧机理和气流流动情况尚不清楚。在实验过程中发现,蒸发管及附近的火焰筒壁面上出现了较严重的积碳现象,影响燃烧室的性能。为了探究该型燃烧室的工作过程、分析积碳现象的原因,采用k-ε湍流模型、旋涡耗散概念燃烧模型(EDC)以及颗粒随机轨道模型对该燃烧室工作流场进行流固热耦合数值计算。结果表明,燃烧室性能参数计算值与台架试车数据较吻合,各项参数相对误差均小于1.7%。计算得到了燃烧室工作时流动和燃烧情况,同时分析出了各气孔流动情况及发挥的作用,并得出了产生积碳现象的原因,为该型燃烧室优化设计提供依据。
A scientific research prototype has a reverse flow combustor with evaporation tube. The combus-tor structure is complex,and the combustion mechanism and airflow are unclear. During the development pro-cess,it was found that carbon deposition occurred on the wall of the evaporator tube and the nearby flame tube,which affected the performance of the combustor. In order to explore the working process of the combustor and an-alyze the cause of carbon deposition,the k-ε turbulence model,Eddy-Dissipation-Concept(EDC)combustionmodel and particle random orbit model were used to calculate the fluid-solid phase coupling of the flow field ofthe combustor. The results show that simulation results are in good agreement with the experimental data,and therelative error of each parameter is less than 1.7%. The flow and combustion of the combustor were calculated,theflow and function of each pore were analyzed,and the cause of carbon deposition was obtained,which provides abasis for the optimal design of the combustor.
A scientific research prototype has a reverse flow combustor with evaporation tube. The combus-tor structure is complex,and the combustion mechanism and airflow are unclear. During the development pro-cess,it was found that carbon deposition occurred on the wall of the evaporator tube and the nearby flame tube,which affected the performance of the combustor. In order to explore the working process of the combustor and an-alyze the cause of carbon deposition,the k-ε turbulence model,Eddy-Dissipation-Concept(EDC)combustionmodel and particle random orbit model were used to calculate the fluid-solid phase coupling of the flow field ofthe combustor. The results show that simulation results are in good agreement with the experimental data,and therelative error of each parameter is less than 1.7%. The flow and combustion of the combustor were calculated,theflow and function of each pore were analyzed,and the cause of carbon deposition was obtained,which provides abasis for the optimal design of the combustor.
引文
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[20]杨卫华,彭建勇,曹俊,等.回流燃烧室复合冷却结构冷却效果研究[J].南京航空航天大学学报,2012,44(6):769-774.
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[22]谭晓茗,赵乃芬,房人麟,等.出流孔复合角对发散孔板冷却效率的影响研究[J].推进技术,2016,37(6):1092-1097.(TAN Xiao-ming,ZHAO Nai-fen,FANG Ren-lin,et al. Research on Cooling Characteristics of Effusion Wall with Compound Angle[J]. Journal of Propulsion Technology,2016,37(6):1092-1097.)
[23]段冬霞,崔玉峰,徐纲,等.某型涡扇发动机燃烧室三维数值模拟[J].燃气轮机技术,2011,24(3):21-26.
[24]阮昌龙,许全宏,孙东文,等.蒸发管蒸发及雾化特性[J].航空动力学报,2012,27(10):2249-2253.
[25]覃文隆,樊未军,张韬,等.微型涡喷发动机蒸发管性能测试及燃烧室数值模拟[J].航空动力学报,2012,27(4):861-867.
[26]王成军,江平,辛欣,等.进气温度对航空发动机辐射换热的影响[J].航空发动机,2013,39(5):31-59.
[27]管承红.燃气轮机高温部件热辐射特性分析[D].哈尔滨:哈尔滨工业大学,2016.
[2] Ibrahim I A,Gad H M,Shabaan M M. Numerical Simulation of Combustion Characteristics of Methane Flame in an Axisymmetric Combustor Model[J]. Global Journal of Engineering Science and Research Management,2014,1(8):115-124.
[3]赵坚行.燃烧的数值模拟[M].北京:科学出版社,2002.
[4]李雅军.环管型燃烧室点火及熄火特性研究[D].哈尔滨:哈尔滨工程大学,2013.
[5] Kez V,Liu F,Consalvi J L,et al. A Comprehensive Evaluation of Different Radiation Models in A Gas Turbine Combustor under Conditions of Oxy-Fuel Combustion with Dry Recycle[J]. Journal of Quantitative Spectroscopy&Radiative Transfer,2016,172:121-133.
[6] Stohr M,Boxx I,Carter C,et al. Dynamics of Lean Blowout of a Swirl-Stabilized Flame in a Gas Turbine Model Combustor[J]. Proceeding of the Combustion Institute. 2011,33(2):2953-2960.
[7]刘亚.燃气轮机真实环形燃烧室大涡模拟[D].大连:大连理工大学,2016.
[8] Rizk N K,Mongia H C. A 3-D Analysis of Gas Turbine Combustor[R]. AIAA 89-2888.
[9] Crooker D S,Smith C E. Numerical Investigation of Angled Dilution Jets in Reverse Flow Gas Turbine Combustor[R]. AIAA 94-2771.
[10]宗超,朱彤.某100kW微燃机燃烧室结构优化及数值模拟[J].燃烧科学与技术,2017,23(1):68-74.
[11]王文萍.燃气轮机高温部件对流/导热/辐射耦合的流动传热机理研究[D].北京:清华大学,2012.
[12]张楷雨.蒸发管燃烧室蒸发特性和贫油熄火极限的研究[D].北京:中国科学院大学,2015.
[13]徐榕.湍流燃烧模型在航空发动机燃烧室中的应用研究[D].南京:南京航空航天大学,2014.
[14]侯晓春,季鹤鸣,严传俊.高性能航空燃气轮机燃烧技术[M].北京:国防工业出版社,2002.
[15] Bharani S,Singh S N,Agrawal D P. Effect of Swirl on the Flow Characteristics in the Outer Annulus of a Prototype Reverse-Flow Gas Turbine Combustor[J]. Experimental Thermal and Fluid Science,2001,25:337-347.
[16] Martino P D,Cinque G. Experimental and Computational Results from an Advanced Reverse-Flow Gas Turbine Combustor[R]. AIAA 95-2999.
[17]胡好生,蔡文祥,赵坚行,等.回流燃烧室燃烧过程的三维数值模拟[J].航空动力学报,2008,23(3):444-449.
[18]蔡文祥,赵坚行,胡好生.回流环形燃烧室反应流场数值模拟[J].航空动力学报,2012,27(3):544-550.
[19]王瑾.小型航空发动机燃烧室参数化数值模拟方法研究[D].南京:南京航空航天大学,2015.
[20]杨卫华,彭建勇,曹俊,等.回流燃烧室复合冷却结构冷却效果研究[J].南京航空航天大学学报,2012,44(6):769-774.
[21]王文波,岳明,杜春雨,等.喷嘴损伤对环形回流燃烧室性能的影响[J].航空动力学报,2017,32(6):1335-1341.
[22]谭晓茗,赵乃芬,房人麟,等.出流孔复合角对发散孔板冷却效率的影响研究[J].推进技术,2016,37(6):1092-1097.(TAN Xiao-ming,ZHAO Nai-fen,FANG Ren-lin,et al. Research on Cooling Characteristics of Effusion Wall with Compound Angle[J]. Journal of Propulsion Technology,2016,37(6):1092-1097.)
[23]段冬霞,崔玉峰,徐纲,等.某型涡扇发动机燃烧室三维数值模拟[J].燃气轮机技术,2011,24(3):21-26.
[24]阮昌龙,许全宏,孙东文,等.蒸发管蒸发及雾化特性[J].航空动力学报,2012,27(10):2249-2253.
[25]覃文隆,樊未军,张韬,等.微型涡喷发动机蒸发管性能测试及燃烧室数值模拟[J].航空动力学报,2012,27(4):861-867.
[26]王成军,江平,辛欣,等.进气温度对航空发动机辐射换热的影响[J].航空发动机,2013,39(5):31-59.
[27]管承红.燃气轮机高温部件热辐射特性分析[D].哈尔滨:哈尔滨工业大学,2016.
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