鸟撞工况下HCA动态拓扑优化整级叶片的数值模拟
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摘要
航空领域中飞机发动机在满足抗鸟撞性能的前提下,实现轻量化是关键问题之一。针对航空发动机冷端风扇叶片,基于HCA算法的动态拓扑优化方法对叶片实现进一步减重,为了验证该动态优化方法的有效性,建立了鸟撞航空发动机整级叶片冲击动力学有限元模型,模拟受气动与离心载荷作用下高速稳定旋转的发动机风扇叶片遭受鸟体撞击的瞬态响应过程。基于LS-DYNA软件平台,对考虑了鸟撞的多工况、多约束条件下叶片的动态优化结果与优化前叶片的多项动态响应指标进行了对比分析,证明了HCA动态拓扑优化方法比传统叶片轻量化方法更为优秀,在满足适航条例强度要求的同时可使叶片减重比达到37.9%,论证了在叶片轻量化设计上基于HCA算法的动态拓扑优化方法的可行性与优越性。
It is always an important issue to improve the light-weight design of aero-engine fan blades in aviation industry,while guaranteeing these blades high level of bird impact resistance. A better distribution of materials in the design of the fan blade was obtained on the basis of the hybrid cellular automaton(HCA)topology optimization method. This method covers multi-constrained conditions and multi-case impacting loads for aeroengine blades under bird strike. The applicability and feasibility of the optimization method was verified according to the simulation of full scale bird impact on the rotating optimized whole blades on LS-DYNA software platform. The finite element model of the optimized whole blade and SPH model of the bird were both established in the simulation. The results of the optimized whole blade of various dynamic responses for bird impact upon different parts proved that the topology optimization using hybrid cellular automaton algorithm for aero-engine fan blades is efficient and practicable. The results showed that it could acquire about 37.9% weight reduction of the aero-engine blade,which is much better than traditional optimization methods.
It is always an important issue to improve the light-weight design of aero-engine fan blades in aviation industry,while guaranteeing these blades high level of bird impact resistance. A better distribution of materials in the design of the fan blade was obtained on the basis of the hybrid cellular automaton(HCA)topology optimization method. This method covers multi-constrained conditions and multi-case impacting loads for aeroengine blades under bird strike. The applicability and feasibility of the optimization method was verified according to the simulation of full scale bird impact on the rotating optimized whole blades on LS-DYNA software platform. The finite element model of the optimized whole blade and SPH model of the bird were both established in the simulation. The results of the optimized whole blade of various dynamic responses for bird impact upon different parts proved that the topology optimization using hybrid cellular automaton algorithm for aero-engine fan blades is efficient and practicable. The results showed that it could acquire about 37.9% weight reduction of the aero-engine blade,which is much better than traditional optimization methods.
引文
[1]贺强,周长春,白晓亮. 3D激光快速成形技术研究[J].机床与液压,2015,43(19):16-18.
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[3]梁春华.高性能航空发动机先进风扇和压气机叶片综述[J].航空发动机,2006,32(3):48-52.
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[11]李琳,薛铮.等强度三维空心叶片的内部拓扑结构[J].航空动力学报,2012,27(10):2329-2335.
[12]蒋向华,王延荣.采用流固耦合方法的整级叶片鸟撞击数值模拟[J].航空动力学报,2008,23(2):299-304.
[13]朱俊,李玉龙.飞机鸟撞试验瞬时速度的连续测试方法研究[J].测控技术,2003,22(12):5-7.
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[20] Benini E. Three-Dimensional Multi-Objective Design Optimization of a Transonic Compressor Rotor[J]. Journal of Propulsion&Power,2003,20(3):559-565.
[21]伊卫林,黄鸿雁,韩万金.基于遗传算法与响应面模型的压气机叶片气动优化设计[J].推进技术,2006,27(6):510-514.(YI Wei-lin,HUANG Hong-yan,HAN Wan-jin. Aerodynamic Design Optimization of Compressor Blade Using Genetic Algorithms and Response Surface Model[J]. Journal of Propulsion Technology,2006,27(6):510-514.)
[22] Tovar A,Patel N M,Niebur G L,et al. Topology Optimization Using a Hybrid Cellular Automation Method with Local Control Rules[J]. Journal of Mechanical Design,2006,128(6):1205-1216.
[23]王冠,周佳,刘志文,等.铝合金汽车前碰撞横梁的轻量化设计与碰撞性能分析[J].中国有色金属学报,2012,22(1):90-98.
[24]聂昕,黄鹏冲,陈涛,等.基于耐撞性拓扑优化的汽车关键安全件设计[J].中国机械工程,2013,24(23):3260-3265.
[25] Whirley R G,Engelmann B E. An Automatic Contact Algorithm in DYNA3D for Impact Problems[C]. Stuttgart:The 21st Structural Mechanics in Reactor Technology,1993.
[26] Georgiadis S,Gunnion A J,Thomson R S,et al. BirdStrike Simulation for Certification of the Boeing 787Composite Moveable Trailing Edge[J]. Composite Structures,2008,86(1):258-268.
[27] Lavoie M A,Gakwaya A,Ensan M N,et al. Validation of Available Approaches for Numerical Bird Strike Modeling Tools[J]. International Review of Mechanical Engineering,2013,1(4).
[28]张海洋,蔚夺魁,王相平,等.鸟撞击风扇转子叶片损伤模拟与试验研究[J].推进技术,2015,36(9):1382-1388.(ZHANG Hai-yang,YU Duo-kui,WANG Xiang-ping,et al. Numerical and Experimental Investigation of Damage of Bird Impact on Fan Blades[J].Journal of Propulsion Technology,2015,36(9):1382-1388.)
[29] Shmotin Y N,Chupin P V,Gabov D V,et al. Bird Strike Analysis of Aircraft Engine Fan[C]. Salzburg:The 7th European LS-DYNA Conference,2009.
[30]何旅洋,郑百林,杨彪,等.航空发动机叶片抗冲击动力学拓扑优化研究[J].力学季刊,2016,(3):513-521.
[31] Mao R,Meguid S A,Teng Y N. Finite Element Modeling of a Bird Striking an Engine Fan Blade[J]. Journal of Aircraft,2012,44(2):583-596.
[2]郑永章.激光快速成型技术在工业设计中的应用与前景[J].装备制造技术,2015,(1):107-108.
[3]梁春华.高性能航空发动机先进风扇和压气机叶片综述[J].航空发动机,2006,32(3):48-52.
[4]刚铁.宽弦空心风扇叶片结构设计及强度分析研究[D].南京:南京航空航天大学,2005.
[5] Mavromihales M,Mason J,Weston W. A Case of Reverse Engineering for the Manufacture of Wide Chord Fan Blades(WCFB)Used in Rolls Royce Aero Engines[J]. Journal of Materials Processing Technology,2003,134(3):279-286.
[6] Fitzgerald G A,T B. The Rolls-Royce Wide Chord Fan Blade[C]. San Francisco:The 1st International Conference of Titanium Development Association,1986.
[7]纪福森,丁拳,李惠莲.某结构空心风扇叶片设计与分析[J].航空发动机,2013,39(4):42-44.
[8]杨剑秋,王延荣.基于正交试验设计的空心叶片结构优化设计[J].航空动力学报,2011,26(2):376-384.
[9]王营,陶智,杜发荣,等.宽弦空心风扇叶片流固耦合作用下的叶片响应分析[J].航空动力学报,2008,23(12):2177-2183.
[10]杨雯,杜发荣,郝勇,等.宽弦空心风扇叶片动力响应特性研究[J].航空动力学报,2007,22(3):444-449.
[11]李琳,薛铮.等强度三维空心叶片的内部拓扑结构[J].航空动力学报,2012,27(10):2329-2335.
[12]蒋向华,王延荣.采用流固耦合方法的整级叶片鸟撞击数值模拟[J].航空动力学报,2008,23(2):299-304.
[13]朱俊,李玉龙.飞机鸟撞试验瞬时速度的连续测试方法研究[J].测控技术,2003,22(12):5-7.
[14]刘大响.航空发动机:飞机的心脏[M].北京:航空工业出版社,2003.
[15] Horsley J. The‘Rolls-Royce’Way of Validating Fan Integrity[C]. Monterey:Joint Propulsion Conference and Exhibit,2013.
[16]刘超,赵振华,陈伟.叶片外物损伤的实验模拟及其疲劳强度的研究[J].推进技术,2014,35(3):403-407.(LIU Chao,ZHAO Zhen-hua,CHEN Wei.Investigations into Simulation Test and Fatigue Strength of Foreign Object Damage of Blades[J]. Journal of Propulsion Technology,2014,35(3):403-407.)
[17] Bends?e M P,Kikuchi E. Generating Optimal Topologies in Structural Design Using a Homogenization Method[J]. Computer Methods in Applied Mechanics&Engineering,1988,71(2):197-224.
[18] Bends?e M P, Sigmund O. Material Interpolation Schemes in Topology Optimization[J]. Archive of Applied Mechanics,1999,69(9-10):635-654.
[19] Xie Y M,Steven G P. Evolutionary Structural Optimization[M]. London:Springer,1997.
[20] Benini E. Three-Dimensional Multi-Objective Design Optimization of a Transonic Compressor Rotor[J]. Journal of Propulsion&Power,2003,20(3):559-565.
[21]伊卫林,黄鸿雁,韩万金.基于遗传算法与响应面模型的压气机叶片气动优化设计[J].推进技术,2006,27(6):510-514.(YI Wei-lin,HUANG Hong-yan,HAN Wan-jin. Aerodynamic Design Optimization of Compressor Blade Using Genetic Algorithms and Response Surface Model[J]. Journal of Propulsion Technology,2006,27(6):510-514.)
[22] Tovar A,Patel N M,Niebur G L,et al. Topology Optimization Using a Hybrid Cellular Automation Method with Local Control Rules[J]. Journal of Mechanical Design,2006,128(6):1205-1216.
[23]王冠,周佳,刘志文,等.铝合金汽车前碰撞横梁的轻量化设计与碰撞性能分析[J].中国有色金属学报,2012,22(1):90-98.
[24]聂昕,黄鹏冲,陈涛,等.基于耐撞性拓扑优化的汽车关键安全件设计[J].中国机械工程,2013,24(23):3260-3265.
[25] Whirley R G,Engelmann B E. An Automatic Contact Algorithm in DYNA3D for Impact Problems[C]. Stuttgart:The 21st Structural Mechanics in Reactor Technology,1993.
[26] Georgiadis S,Gunnion A J,Thomson R S,et al. BirdStrike Simulation for Certification of the Boeing 787Composite Moveable Trailing Edge[J]. Composite Structures,2008,86(1):258-268.
[27] Lavoie M A,Gakwaya A,Ensan M N,et al. Validation of Available Approaches for Numerical Bird Strike Modeling Tools[J]. International Review of Mechanical Engineering,2013,1(4).
[28]张海洋,蔚夺魁,王相平,等.鸟撞击风扇转子叶片损伤模拟与试验研究[J].推进技术,2015,36(9):1382-1388.(ZHANG Hai-yang,YU Duo-kui,WANG Xiang-ping,et al. Numerical and Experimental Investigation of Damage of Bird Impact on Fan Blades[J].Journal of Propulsion Technology,2015,36(9):1382-1388.)
[29] Shmotin Y N,Chupin P V,Gabov D V,et al. Bird Strike Analysis of Aircraft Engine Fan[C]. Salzburg:The 7th European LS-DYNA Conference,2009.
[30]何旅洋,郑百林,杨彪,等.航空发动机叶片抗冲击动力学拓扑优化研究[J].力学季刊,2016,(3):513-521.
[31] Mao R,Meguid S A,Teng Y N. Finite Element Modeling of a Bird Striking an Engine Fan Blade[J]. Journal of Aircraft,2012,44(2):583-596.