浮动壁式火焰筒壁温优化研究
|
摘要
浮动壁结构的燃烧室可以有效改善火焰筒壁温分布和提高冷却效果,是提高航空发动机推重比的一项重要技术。本文将遗传算法与代理模型技术相结合,建立了代理模型-遗传优化方法,并将该方法应用于浮动壁壁温优化分析,得到一种具有冷却效果好、壁温分布平稳的最优浮动壁结构。与此同时,本文开展了几何参数对浮动壁壁温分布影响的研究。本文研究工作主要包括:
1.开展浮动壁壁温的数值仿真计算技术研究。通过对浮动壁结构的研究,建立了浮动壁式火焰筒的参数化几何模型;实现了高质量结构化网格的自动划分;选择整场求解的方法以及适当的简化模型求解浮动壁壁温并实现浮动壁壁温数值计算的自动运行;并通过与现有实验结果的对比分析,验证本文数值仿真研究方法的正确性。
2.开展浮动壁壁温优化的优化方法研究。建立了浮动壁壁温优化模型;将代理模型与标准遗传算法结合,建立一种适用于浮动壁壁温优化的代理模型-遗传优化方法;以ISIGHT软件为平台,实现浮动壁壁温优化的优化流程,并且通过算例验证本文优化方法在浮动壁壁温优化中的适用性。
3.在给定气动参数下,对六种浮动壁结构方案进行壁温优化分析,得到最优浮动壁结构;同时,进一步分析研究了孔间距、孔径、冲击高度、气膜孔角度等几何变量对浮动壁壁温分布的影响规律。
The combustor with floatwall can effectively improve the wall temperature’s distribution and cooling effect.It’s an important technology for aero-engine to improve its power-to-weight. In this paper, genetic algorithms and approximate model are combined to establish a approximate model-genetic optimization method, and the method is applied to optimize the floatwall’s wall temperature, obtained the floatwall structure with a better cooling effect and optimal wall temperature distribution. At the same time, systematic study about the geometric parameters on the floatwall’s wall temperature distribution of impact n was done. This paper study work mainly included the following:
1.Carry out the numerical simulation technology research about the floatwall’s wall temperature. By the studies about the floatwall structure, the parametric geometric model of the combustor with floatwall was established;the high quality structured grid was achieved automaticly; Select the entire field calculation methods and a appropriate simplified model for solving the floatwall’s wall temperature,and the floatwall’s wall temperature values was calculated automatically; by comparison with existing experimental results, the results show that computing precision and efficiency of the numerical simulation model are good.
2.In order to complete the the optimization about the floatwall’s wall temperature more effectively, an optimization method that combines approximate model and genetic algorithm was put forward.The optimization results show that this method not only computing high efficiency and convergency,but also the relationship between the objective function and design variable can be studied based on the data obtained from the experimental design points.
3.Under the certain conditions of aerodynamic parameters, respectively for the numerical simulation model about the floatwall with different hole spacing and angel of film cooling holes ,the optimization work about the wall tempreture was done.The optimal geometric parameters of the floating wall was obtained;at the same time, systematic study about the geometric parameters on the objective function was done.
1.开展浮动壁壁温的数值仿真计算技术研究。通过对浮动壁结构的研究,建立了浮动壁式火焰筒的参数化几何模型;实现了高质量结构化网格的自动划分;选择整场求解的方法以及适当的简化模型求解浮动壁壁温并实现浮动壁壁温数值计算的自动运行;并通过与现有实验结果的对比分析,验证本文数值仿真研究方法的正确性。
2.开展浮动壁壁温优化的优化方法研究。建立了浮动壁壁温优化模型;将代理模型与标准遗传算法结合,建立一种适用于浮动壁壁温优化的代理模型-遗传优化方法;以ISIGHT软件为平台,实现浮动壁壁温优化的优化流程,并且通过算例验证本文优化方法在浮动壁壁温优化中的适用性。
3.在给定气动参数下,对六种浮动壁结构方案进行壁温优化分析,得到最优浮动壁结构;同时,进一步分析研究了孔间距、孔径、冲击高度、气膜孔角度等几何变量对浮动壁壁温分布的影响规律。
The combustor with floatwall can effectively improve the wall temperature’s distribution and cooling effect.It’s an important technology for aero-engine to improve its power-to-weight. In this paper, genetic algorithms and approximate model are combined to establish a approximate model-genetic optimization method, and the method is applied to optimize the floatwall’s wall temperature, obtained the floatwall structure with a better cooling effect and optimal wall temperature distribution. At the same time, systematic study about the geometric parameters on the floatwall’s wall temperature distribution of impact n was done. This paper study work mainly included the following:
1.Carry out the numerical simulation technology research about the floatwall’s wall temperature. By the studies about the floatwall structure, the parametric geometric model of the combustor with floatwall was established;the high quality structured grid was achieved automaticly; Select the entire field calculation methods and a appropriate simplified model for solving the floatwall’s wall temperature,and the floatwall’s wall temperature values was calculated automatically; by comparison with existing experimental results, the results show that computing precision and efficiency of the numerical simulation model are good.
2.In order to complete the the optimization about the floatwall’s wall temperature more effectively, an optimization method that combines approximate model and genetic algorithm was put forward.The optimization results show that this method not only computing high efficiency and convergency,but also the relationship between the objective function and design variable can be studied based on the data obtained from the experimental design points.
3.Under the certain conditions of aerodynamic parameters, respectively for the numerical simulation model about the floatwall with different hole spacing and angel of film cooling holes ,the optimization work about the wall tempreture was done.The optimal geometric parameters of the floating wall was obtained;at the same time, systematic study about the geometric parameters on the objective function was done.
引文
[1]刘殿春,浮动壁燃烧室技术的发展和应用,国际航空,2004(1):50~51
[2]金如山,航空燃气轮机燃烧室,宇航出版社,1988
[3]侯晓春,季鹤鸣等,高性能航空燃气轮机燃烧技术,国防工业出版社,2002
[4]刘军,航空发动机的先进燃烧室技术,国际航空,1997.12:48~50
[5]陶文铨,数值传热学,西安交通大学出版社,2001年:483~488
[6]许全宏,张宝华,林宇震,刘高恩,冲击加多斜孔双层壁冷却方式气膜绝热温比研究,航空动力学报,2000年10月第15卷第4期:
[7]许全宏,林宇震,刘高恩,冲击加多斜孔双层壁冷却方式冲击换热系数,大连理工大学学报,2001年11月第41卷
[8]许全宏,林宇震,刘高恩,冲击-发散复合冷却方式发散壁换热系数研究,航空动力学报,2004年4月第19卷第2期
[9]胡超,许全宏,徐剑等,冲击-发散冷却壁温分布和冷却效率研究,航空动力学报,2008年10月第23卷第10期
[10]王磊,张靖周,杨卫华等,冲击-发散冷却气膜冷却效率的实验研究,中国工程热物理学会第十二届年会,2006
[11]宋双文,杨卫华,胡好生等,冲击+逆向对流+气膜冷却传热特性的研究,航空动力学报,2007年9月第22卷第9期
[12]许全宏,林宇震,刘高恩,主燃烧室冲击-发散双层壁冷却方式壁温验证试验研究,航空动力学报,2005年4月第20卷第2期
[13]俞伯良,李继保,单、双层壁火焰筒壁面冷却效果比较试验研究,燃气涡轮试验与研究。1999年第12卷第2期
[14]李彬,吉洪湖,江义军,冲击-发散冷却火焰筒浮动瓦片三维壁温计算分析,航空动力学报,2007年3月第22卷第3期
[15]李彬,吉洪湖,江义军等,燃烧室壁冲击-逆向对流-气膜冷却特性的数值研究,航空动力学报,2007年3月第22卷第3期
[16]谢浩,阵列射流冲击冷却换热系数的数值研究,能源研究与利用,2005,5
[17] Mellor.A.M., Design of Modern Turbine Combustor, Academic Press, 1990
[18] Bazdidi-Tehran.F. and Andrews.G.E., Full Coverage Discrete Hole Film Cooling,Investigation of the Effect of Variable Density Ratio, Journal of Engineering for Gas Turbines and Power, Vol.116, pp587-596, 1994
[19] Champion.J.L. and Deshaies.B., Experimental Investigation of the Wall Flow and Cooling of Combustion Chamber Walls, AIAA 95-2498, 1995
[20] Andrews, G. E., Al Dabagh, A. M. and Asere, A. A., Impingement/Effusion Cooling, AGARD CP 527,“Heat Transfer and Cooling in Gas Turbine”, pp30.1– 30.10, 1992
[21] Al Dabagh.A.M., Andrews.G.E., Abdul Husain.R.A..A. and Husain.C. I.,Impingement/Effusion Cooling: The Influence of the Number of Impingement Holes and Pressure Loss on the Heat Transfer Coefficient, ASME Paper No.89-GT-188, 1989
[22] Cho.H.H. and Rhee.D. H., Local Heat/Mass Transfer Measurements on the Effusion Plate in Impingement/Effusion Cooling System, ASME 2000-GT-0252, 2000
[23] Cho, H.H., Rhee.D. H. and Goldstein. R. J., Effect of Hole Arrangements on Local Heat/Mass Transfer for Impingement/Effusion Cooling With Small Hole Spacing, ASME GT2004-53685, 2004
[24] Rhee.D.H., Choi. J. H. and Cho. H. H., Flow and Heat (Mass) Transfer Characteristics in an Impingement/Effusion Cooling System With Crossflow, ASME GT2002-30474, 2002
[25]赵清杰,李彬,浮动瓦块冷却结构在燃烧室中的应用和发展,燃气涡轮试验与研究,2001.14(1):10-13
[26] Peter.H., David.T. , James.W.G. and Jobn.N.B. , Experimental Flow Characteristics of a Single Turbulent Jet Impinging on a Flat Plate, NASA TN D-5690, 1970
[27]刘高恩、吴文东主编,高效节能发动机文集(第四分册),航空工业出版社,1991
[28]张宏建,崔海涛,温卫东,平板结构支撑杆位置优化分析研究,第十二届航空发动机结构强度振动会议论文集,四川,成都,2004.9;
[29]石炜,崔海涛,温卫东,基于模糊推理的遗传算法,南京航空航天大学第七届研究生学术会议,2005年11月
[30]王丽婧,崔海涛,温卫东,免疫遗传算法及其在结构优化中的应用,南京航空航天大学第八届研究生学术会议,2006年11月
[31]蔡文祥,胡好生,赵坚行,环形燃烧室火焰筒及旋流器流场计算,工程热物理学报,2005
[32]程勇,汪军,火焰筒内环向多孔径向射流的流场研究,热力透平,2005
[33]徐行,黄勇,燃烧室流动的数值计算,航空动力学报,1997
[34]邢玉明,赵云惠,王丰,某发动机气膜冷却火焰筒壁温的数值计算,北京航空航天大学学报,1997
[35]杨志民,韩振兴,燃烧室火焰筒壁温三维数值分析,航空发动机,1998
[36]何立明,曹平,李长林等,计算席壁结构火焰筒壁温的另一种方法射,推进技术,1995
[37]董志锐,刘高文,胡正义,双层壁火焰筒二维壁温计算,燃气涡轮试验与研究,1999
[38]冀春俊,徐世泊,于飞,燃气轮机燃烧室内部两相流动数值模拟与结构优化,动力工程,2004
[39]王卫国,李永康,李彬,环形燃烧室火焰筒壁面结构优化初探,燃气涡轮试验与研究,1999
[40]张丽芬,采用热流耦合方法对内冷式涡轮叶片换热的计算研究,西北工业大学硕士论文,2006
[41] Yuyang Lai,Xin Yuan,Blade Design Optimization With Three-Dimensional Viscous Analyses and Hybrid Optimization Approach,9th AIAA/ISSMO Symposium on Multidisciplinary Analysis and Optimization,Atlanta,USA,Sept 4-6,2002.AIAA No. AIAA-2002-5658
[42]隋洪涛,陈红全,多目标翼型优化设计基因算法研究,空气动力学学报,Vol.18,No.2,236一240,2000.
[43]石秀华,孟祥众,杜向党等,基于多岛遗传算法的振动控制传感器优化配置,振动、测试与诊断,2008年3月第28卷第一期
[44]曾会华,余雄庆,基于代理模型的气动外形优化,航空计算技术.Vol.35,NO.4,2005年11月
[45] Yuehua Gao,Xicheng Wang.An effeetive warpage optimization method in injection molding based on kriging model.Intemational Journal of Advaneed Manufacturing Technology,2008 37(9):953一960
[46]邓文剑,楚武利,吴艳辉等,基于试验设计近似模型优化方法及其在离心泵上的应用,2008年12月第26卷第6期
[47]赵周鹏,无人机机翼气动与结构优化设计研究,南京航空航天大学第八届研究生学术会议论文集,2006年
[48]王亮,王竣涛,任利,基于ISIGHT的手机模型优化,计算机技术与自动化,2006.6
[49]马静敏,沈友徽,李华,基于ISIGHT的油船槽形横舱壁优化设计,船海工程,2005.1
[50] Holland.J.H. ,Genetic algorithms and the Optimal Alllocation of Trials,SIAM Journal on Computing.Vol.2,No.2,1973,pp.88-103
[51] Giunta.A.A,Wojtkiewicz.Jr.S.F,Eldred.M.S.,Overview of Modern Design of Experiments Methods for Computational Simulations[R]. AIAA 2003
[52] Golovidov,Response Surfaee Approximations for Aerodynamic Parameters in High Speed Civil TransPort Optimization,Technical Report ncstrl.vateeh_cs//TR-97-15,Computer Science,Vrginia Polytechnic Institute and State University
[53] Anthony.A.Giunta.,Aircraft Multidisciplinary Design Optimization Using Design of Experiments Theory and Response Surface Modeling Methods. , PhD dissertation,Virginia Polytechnic Institute,May 1997
[2]金如山,航空燃气轮机燃烧室,宇航出版社,1988
[3]侯晓春,季鹤鸣等,高性能航空燃气轮机燃烧技术,国防工业出版社,2002
[4]刘军,航空发动机的先进燃烧室技术,国际航空,1997.12:48~50
[5]陶文铨,数值传热学,西安交通大学出版社,2001年:483~488
[6]许全宏,张宝华,林宇震,刘高恩,冲击加多斜孔双层壁冷却方式气膜绝热温比研究,航空动力学报,2000年10月第15卷第4期:
[7]许全宏,林宇震,刘高恩,冲击加多斜孔双层壁冷却方式冲击换热系数,大连理工大学学报,2001年11月第41卷
[8]许全宏,林宇震,刘高恩,冲击-发散复合冷却方式发散壁换热系数研究,航空动力学报,2004年4月第19卷第2期
[9]胡超,许全宏,徐剑等,冲击-发散冷却壁温分布和冷却效率研究,航空动力学报,2008年10月第23卷第10期
[10]王磊,张靖周,杨卫华等,冲击-发散冷却气膜冷却效率的实验研究,中国工程热物理学会第十二届年会,2006
[11]宋双文,杨卫华,胡好生等,冲击+逆向对流+气膜冷却传热特性的研究,航空动力学报,2007年9月第22卷第9期
[12]许全宏,林宇震,刘高恩,主燃烧室冲击-发散双层壁冷却方式壁温验证试验研究,航空动力学报,2005年4月第20卷第2期
[13]俞伯良,李继保,单、双层壁火焰筒壁面冷却效果比较试验研究,燃气涡轮试验与研究。1999年第12卷第2期
[14]李彬,吉洪湖,江义军,冲击-发散冷却火焰筒浮动瓦片三维壁温计算分析,航空动力学报,2007年3月第22卷第3期
[15]李彬,吉洪湖,江义军等,燃烧室壁冲击-逆向对流-气膜冷却特性的数值研究,航空动力学报,2007年3月第22卷第3期
[16]谢浩,阵列射流冲击冷却换热系数的数值研究,能源研究与利用,2005,5
[17] Mellor.A.M., Design of Modern Turbine Combustor, Academic Press, 1990
[18] Bazdidi-Tehran.F. and Andrews.G.E., Full Coverage Discrete Hole Film Cooling,Investigation of the Effect of Variable Density Ratio, Journal of Engineering for Gas Turbines and Power, Vol.116, pp587-596, 1994
[19] Champion.J.L. and Deshaies.B., Experimental Investigation of the Wall Flow and Cooling of Combustion Chamber Walls, AIAA 95-2498, 1995
[20] Andrews, G. E., Al Dabagh, A. M. and Asere, A. A., Impingement/Effusion Cooling, AGARD CP 527,“Heat Transfer and Cooling in Gas Turbine”, pp30.1– 30.10, 1992
[21] Al Dabagh.A.M., Andrews.G.E., Abdul Husain.R.A..A. and Husain.C. I.,Impingement/Effusion Cooling: The Influence of the Number of Impingement Holes and Pressure Loss on the Heat Transfer Coefficient, ASME Paper No.89-GT-188, 1989
[22] Cho.H.H. and Rhee.D. H., Local Heat/Mass Transfer Measurements on the Effusion Plate in Impingement/Effusion Cooling System, ASME 2000-GT-0252, 2000
[23] Cho, H.H., Rhee.D. H. and Goldstein. R. J., Effect of Hole Arrangements on Local Heat/Mass Transfer for Impingement/Effusion Cooling With Small Hole Spacing, ASME GT2004-53685, 2004
[24] Rhee.D.H., Choi. J. H. and Cho. H. H., Flow and Heat (Mass) Transfer Characteristics in an Impingement/Effusion Cooling System With Crossflow, ASME GT2002-30474, 2002
[25]赵清杰,李彬,浮动瓦块冷却结构在燃烧室中的应用和发展,燃气涡轮试验与研究,2001.14(1):10-13
[26] Peter.H., David.T. , James.W.G. and Jobn.N.B. , Experimental Flow Characteristics of a Single Turbulent Jet Impinging on a Flat Plate, NASA TN D-5690, 1970
[27]刘高恩、吴文东主编,高效节能发动机文集(第四分册),航空工业出版社,1991
[28]张宏建,崔海涛,温卫东,平板结构支撑杆位置优化分析研究,第十二届航空发动机结构强度振动会议论文集,四川,成都,2004.9;
[29]石炜,崔海涛,温卫东,基于模糊推理的遗传算法,南京航空航天大学第七届研究生学术会议,2005年11月
[30]王丽婧,崔海涛,温卫东,免疫遗传算法及其在结构优化中的应用,南京航空航天大学第八届研究生学术会议,2006年11月
[31]蔡文祥,胡好生,赵坚行,环形燃烧室火焰筒及旋流器流场计算,工程热物理学报,2005
[32]程勇,汪军,火焰筒内环向多孔径向射流的流场研究,热力透平,2005
[33]徐行,黄勇,燃烧室流动的数值计算,航空动力学报,1997
[34]邢玉明,赵云惠,王丰,某发动机气膜冷却火焰筒壁温的数值计算,北京航空航天大学学报,1997
[35]杨志民,韩振兴,燃烧室火焰筒壁温三维数值分析,航空发动机,1998
[36]何立明,曹平,李长林等,计算席壁结构火焰筒壁温的另一种方法射,推进技术,1995
[37]董志锐,刘高文,胡正义,双层壁火焰筒二维壁温计算,燃气涡轮试验与研究,1999
[38]冀春俊,徐世泊,于飞,燃气轮机燃烧室内部两相流动数值模拟与结构优化,动力工程,2004
[39]王卫国,李永康,李彬,环形燃烧室火焰筒壁面结构优化初探,燃气涡轮试验与研究,1999
[40]张丽芬,采用热流耦合方法对内冷式涡轮叶片换热的计算研究,西北工业大学硕士论文,2006
[41] Yuyang Lai,Xin Yuan,Blade Design Optimization With Three-Dimensional Viscous Analyses and Hybrid Optimization Approach,9th AIAA/ISSMO Symposium on Multidisciplinary Analysis and Optimization,Atlanta,USA,Sept 4-6,2002.AIAA No. AIAA-2002-5658
[42]隋洪涛,陈红全,多目标翼型优化设计基因算法研究,空气动力学学报,Vol.18,No.2,236一240,2000.
[43]石秀华,孟祥众,杜向党等,基于多岛遗传算法的振动控制传感器优化配置,振动、测试与诊断,2008年3月第28卷第一期
[44]曾会华,余雄庆,基于代理模型的气动外形优化,航空计算技术.Vol.35,NO.4,2005年11月
[45] Yuehua Gao,Xicheng Wang.An effeetive warpage optimization method in injection molding based on kriging model.Intemational Journal of Advaneed Manufacturing Technology,2008 37(9):953一960
[46]邓文剑,楚武利,吴艳辉等,基于试验设计近似模型优化方法及其在离心泵上的应用,2008年12月第26卷第6期
[47]赵周鹏,无人机机翼气动与结构优化设计研究,南京航空航天大学第八届研究生学术会议论文集,2006年
[48]王亮,王竣涛,任利,基于ISIGHT的手机模型优化,计算机技术与自动化,2006.6
[49]马静敏,沈友徽,李华,基于ISIGHT的油船槽形横舱壁优化设计,船海工程,2005.1
[50] Holland.J.H. ,Genetic algorithms and the Optimal Alllocation of Trials,SIAM Journal on Computing.Vol.2,No.2,1973,pp.88-103
[51] Giunta.A.A,Wojtkiewicz.Jr.S.F,Eldred.M.S.,Overview of Modern Design of Experiments Methods for Computational Simulations[R]. AIAA 2003
[52] Golovidov,Response Surfaee Approximations for Aerodynamic Parameters in High Speed Civil TransPort Optimization,Technical Report ncstrl.vateeh_cs//TR-97-15,Computer Science,Vrginia Polytechnic Institute and State University
[53] Anthony.A.Giunta.,Aircraft Multidisciplinary Design Optimization Using Design of Experiments Theory and Response Surface Modeling Methods. , PhD dissertation,Virginia Polytechnic Institute,May 1997