出流孔倾角对层板冷却结构流动与换热特性的影响
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摘要
设计了5种不同层板冷却结构出流孔倾角模型,应用Fluent软件对其进行流动与换热的耦合计算,并对数值计算结果进行了对比分析。结果表明:当冷流沿出流孔流入主流时,冷流与热流掺混较强,湍动能沿程逐渐增大;随后掺混逐渐趋于平稳,湍动能逐渐减小;随着出流孔倾角的逐渐增大;出流孔中心线两侧的流体不断被卷吸进来,不断挤压出流孔中心线上的流体,冷流与热流的混合增强,掺混核心区的面积逐渐增大。随着出流孔倾角的逐渐增大,沿出流孔流入主流的冷流覆盖在热侧壁面上的温度逐渐升高,换热逐渐减弱,热侧壁面温度逐渐升高。
Five different lamilloy configurations model in which the flow angle of hole were changed were designed to conjugate simulate the flow and heat transfer characteristics with fluent software,and the results were analyzed by comparison. The results showed that when the cool air flow into the mainstream along the hole of flow,cool air and hot air mix stronger and turbulence kinetic energy increases along the way. Then the mixing gradually stabilizes,the turbulent kinetic energy decreases gradually.With the gradually increase of the flow angle of hole,the fluid on the both sides of the center line of the hole is sucked in continuous,and the fluid on the center line of the hole is squeezed out in contin-uous,which enhances cool air and hot air mixing and increases the proportion of mixing core area.With the gradually increase of the flow angle of hole,the temperature of cool air which is covered on the hot side surface increases gradually,and heat transfer are weakened and the temperature of hot side surface are increased gradually.
Five different lamilloy configurations model in which the flow angle of hole were changed were designed to conjugate simulate the flow and heat transfer characteristics with fluent software,and the results were analyzed by comparison. The results showed that when the cool air flow into the mainstream along the hole of flow,cool air and hot air mix stronger and turbulence kinetic energy increases along the way. Then the mixing gradually stabilizes,the turbulent kinetic energy decreases gradually.With the gradually increase of the flow angle of hole,the fluid on the both sides of the center line of the hole is sucked in continuous,and the fluid on the center line of the hole is squeezed out in contin-uous,which enhances cool air and hot air mixing and increases the proportion of mixing core area.With the gradually increase of the flow angle of hole,the temperature of cool air which is covered on the hot side surface increases gradually,and heat transfer are weakened and the temperature of hot side surface are increased gradually.
引文
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[17]全栋梁,刘松龄,李江海,等.层板冷却特性的实验与数值模拟研究[J].推进技术,2004(2):134-138.
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[19]王鸣,卢元丽,吉洪湖.冲击孔对层板冷却叶片前缘传热影响的数值研究[J].航空动力学报,2013(10):2240-2247.
[20]全栋梁,刘松龄,李江海.层板冷却结构传热优化数值模拟研究[J].西北工业大学学报,2004(6):816-820.
[21]聂建豪,朱惠人,任战鹏.对层板冷却效率随主流流动方向变化的数值研究[J].机械与电子,2013(9):71-73.
[22]郁新华,刘松龄,董志锐.航空发动机层板冷却结构的内流阻特性的试验研究[J].燃气涡轮试验与研究,2000(3):22-26.
[23]吴向宇,黎旭,时艳,等.典型层板冷却结构热疲劳破坏特性研究[J].航空动力学报,2014(5):1177-1183.
[24]胡娅萍,卢元丽,吉洪湖,等.层板冷却涡轮叶片前缘内部流动与传热特性实验[J].航空动力学报,2014(2):241-249.
[2]侯晓春,季鹤鸣.高性能航空燃气轮机燃烧技术[M].北京:国防工业出版社,2002.
[3]刘军.航空发动机的先进燃烧室技术[J].国际航空,1997(12):48-50.
[4]Nealy D B,Reider S.Evaluation of Laminated Porous Wall Materials for Combustor Liner Cooling[J].Journal of Engineering for Power-Transactions of the ASME,1980,102(2):268-276.
[5]Eriksen V L.Film Cooling Effectiveness and Heat Transfer with Injection through Holes[Z].USA:[s.n.],1971:179.
[6]Rolls-Royce Aero Space Group.喷气发动机[M].北京:罗尔斯-罗伊斯公司,1986.
[7]Funazaki K,Hachiya K.Systematic numerical studies on heat transfer and aerodynamic characteristics of impingement cooling devices combined with pins[C]//ASME Turbo Expo.USA:[s.n..],2003:16-19.
[8]Favaretto C F F,Funazaki K.Application of genetic algorithms to design of an internal turbine cooling system[C]//ASME Turbo Expo 2003.USA:[s.n.],2003:273-278.
[9]郁新华,全栋梁,刘松龄,等.层板结构冷却有效性的研究[J].航空动力学报,2003,18(5):615-622.
[10]陶智,魏豪杰,丁水汀,等.典型层板冷却结构中流体流阻与换热特性的实验[J].航空动力学报,2007,22(2):193-198.
[11]全栋梁,刘松龄,李江海,等.多孔层板冷却有效性的研究[J].航空动力学报,2004(4):520-524.
[12]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[J].航空动力学报,2004,19(2):213-218.
[13]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[J].航空动力学报,2007,22(9):1417-1422.
[14]袁星,吕东.扰流柱几何参数对层板流阻和换热特性的影响[J].航空动力学报,2009,24(5):1016-1021.
[15]曹俊,熊纯,杨卫华,等.回流燃烧室弯曲段冲击扰流柱+逆向对流+气膜冷却效率[J].南京航空航天大学学报,2011,43(2):178-183.
[16]谭晓茗,李业芳,张靖周.致密多孔层板冷却结构研究[J].机械工程学报,2012,48(12):144-149.
[17]全栋梁,刘松龄,李江海,等.层板冷却特性的实验与数值模拟研究[J].推进技术,2004(2):134-138.
[18]全栋梁,刘松龄,李江海.层板冷却结构强化换热机理[J].航空动力学报,2004(6):860-865.
[19]王鸣,卢元丽,吉洪湖.冲击孔对层板冷却叶片前缘传热影响的数值研究[J].航空动力学报,2013(10):2240-2247.
[20]全栋梁,刘松龄,李江海.层板冷却结构传热优化数值模拟研究[J].西北工业大学学报,2004(6):816-820.
[21]聂建豪,朱惠人,任战鹏.对层板冷却效率随主流流动方向变化的数值研究[J].机械与电子,2013(9):71-73.
[22]郁新华,刘松龄,董志锐.航空发动机层板冷却结构的内流阻特性的试验研究[J].燃气涡轮试验与研究,2000(3):22-26.
[23]吴向宇,黎旭,时艳,等.典型层板冷却结构热疲劳破坏特性研究[J].航空动力学报,2014(5):1177-1183.
[24]胡娅萍,卢元丽,吉洪湖,等.层板冷却涡轮叶片前缘内部流动与传热特性实验[J].航空动力学报,2014(2):241-249.