基于打靶试验的风扇机匣包容能力评估方法
|
摘要
为保障飞行安全,航空发动机机匣需具有足够的抗冲击能力以包容高速旋转状态下丢失的叶片。针对某型涡扇发动机对开式风扇机匣包容性评估需求,提出了1种结合真实机匣打靶试验和有限元分析评估机匣包容能力的方法。通过使用真实机匣和真实叶片进行打靶试验获得风扇机匣的冲击损伤情况,并基于ANSYS/LS-DYNA进行了瞬态动力学有限元分析。结果表明:采用Johnson-Cook模型预测的机匣伤形状、尺寸以及叶片残余速度均与试验结果接近,验证了数值分析方法的准确性。采用验证过的数值分析方法开展旋转状态下机匣的包容性评估,发现由于撞击姿态差异和失效模式转变,风扇机匣可以包容以100%工作转速飞出的叶片,但机匣出现长裂纹,接近临界包容状态。所提出的方法可以在不具备部件包容试验条件的情况下,以较方便的形式对机匣包容能力可靠评估。
In order to ensure flight safety,the aeroengine casing must have sufficient impact resistance to contain the loss of blades at high speed rotation. In order to meet the needs of an split fan casing containment evaluation of a engine, a new method was proposed to evaluate the casing containment capability in combination with real casing ballistic impact test and finite element analysis. The impact damage of fan casing was obtained by using real casing and real ballistic impact test,and the transient dynamic finite element analysis based on ANSYS/LS-DYNA was carried out. The results show that the casing damage shape,size and blade residual velocity predicted by Johnson-Cook model are close to the experimental results,and the accuracy of the numerical analysis method is verified. The validated numerical analysis method is adopted to launch the casing containment evaluation in rotating state. Due to the difference of impact attitude and the change of failure mode,the fan casing can contain the blade flying out at 100% working speed,but the casing appears long cracks,which are close to the critical containment state. The proposed method can be used to evaluate the containment capability of the casing in a more convenient form without the test conditions of component containment.
In order to ensure flight safety,the aeroengine casing must have sufficient impact resistance to contain the loss of blades at high speed rotation. In order to meet the needs of an split fan casing containment evaluation of a engine, a new method was proposed to evaluate the casing containment capability in combination with real casing ballistic impact test and finite element analysis. The impact damage of fan casing was obtained by using real casing and real ballistic impact test,and the transient dynamic finite element analysis based on ANSYS/LS-DYNA was carried out. The results show that the casing damage shape,size and blade residual velocity predicted by Johnson-Cook model are close to the experimental results,and the accuracy of the numerical analysis method is verified. The validated numerical analysis method is adopted to launch the casing containment evaluation in rotating state. Due to the difference of impact attitude and the change of failure mode,the fan casing can contain the blade flying out at 100% working speed,but the casing appears long cracks,which are close to the critical containment state. The proposed method can be used to evaluate the containment capability of the casing in a more convenient form without the test conditions of component containment.
引文
[1]Sarkar S,Atluri S N.Effects of multiple blade interaction on the containment of blade fragments during a rotor failure[J].Finite Elements in Analysis and Design,1996,23:211-223.
[2]宣海军,陆晓,洪伟荣,等.航空发动机机匣包容性研究综述[J].航空动力学报,2010,25(8):1860-1870.XUAN Haijun,LU Xiao,HONG Weirong,et al.Review of aero-engine case containment research[J].Journal of Aerospace Power,2010,25(8):1860-1870.(in Chinese)
[3]马艳红,梁智超,王桂华,等.航空发动机叶片丢失问题研究综述[J].航空动力学报,2016(3):513-526.MA Yanhong,LIANG Zhichao,WANG Guihua,et al.Review on the blade loss of aero-engine[J].Journal of Aerospace Power,2016(3):513-526.(in Chinese)
[4]FAR33 Airworthiness standards:Aircraft engines[S].United States:Federal Aviation Administration,1984.
[5]中国民用航空总局.CCAR-33航空发动机适航规定[S].北京:中国民用航空总局,2005:78-79.Civil Aviation Administration of China.CCAR-33 Aviation engine airworthiness regulation[S].Beijing:Civil Aviation Administration of China,2005:78-79.(in Chinese)
[6]国防科学技术工业委员会.GJB 3366航空涡轮发动机包容性要求[S].北京:国防科学技术工业委员会,1998:1-3.Commission of Science.Technology and Industry for National Defense.GJB 3366 The requirements of aircraft turbine engine containment[S].Beijing:Commission of Science.Technology and Industry for National Defense,1998:1-3.(in Chinese)
[7]Xuan H,Wu R.Aeroengine turbine blade containment tests using high-speed rotor spin testing facility[J].Aerospace Science and Technology,2006,10(6):501-508.
[8]He Q,Xuan H,Liu L,et al.Perforation of aero-engine fan casing by a single rotating blade[J].Aerospace Science and Technology,2013,25(1):234-241.
[9]He Q,Xie Z,Xuan H,et al.Multi-blade effects on aero-engine blade containment[J].Aerospace Science and Technology,2016.49:101-111.
[10]Teng X,Wierzbicki T.Gouging and fracture of engine containment structure under fragment impact[J].Journal of Aerospace Engineering,2008,21(3):174-186.
[11]Kraus A,Frischbier J.Containment and penetration in case of blade loss in a low pressure turbine[C]//DYNAmore LS-DYNA Forum.Bad Mergentheim,September,2002.
[12]He Q,Xuan H,Liao L,et al.,Simulation methodology development for rotating blade containment analysis[J].Journal of Zhejiang University-SCIENCE A,2012,13(4):239-259.
[13]Sarkar S,Atluri S N.Effects of multiple blade interaction on the containment of blade fragments during a rotor failure[J].Finite Elements in Analysis and Design,1996,23(2-4):211-223.
[14]Hermosilla U,Alcaraz J L,Aja A M.Blade impact simulation against turbine casings[C]//2004 ABAQUS Users’Conference,Boston,MAUSA,2004.
[15]于亚彬,陈伟.模型机匣/叶片的包容性数值分析[J].航空动力学报,2005,20(3):429-433.YU Yabin,CHEN Wei.Numerical analysis of the modeled blade/casing containment[J].Journal of Aerospace Power,2005,20(3):429-433.(in Chinese)
[16]于连超,陈伟,关玉璞,等.多层机匣的包容性数值仿真研究[J].航空发动机,2009,35(4):32-35.YU Lianchao,CHEN Wei,GUAN Yupu,et al.Numerical simulation of multiplelayer casing containment[J].Aeroengine,2009,35(4):32-35.(in Chinese)
[17]Ambur D R,Jaunky N,Lawson R E,et al.A gas actuated projectile launcher for high energy impact testing of structure[R].A-IAA-99-1385.
[18]Ambur D R,Jaunky N,Lawson R E,et al.Numerical simulations for high-energy impact of thin plates[J].International Journal of Impact Engineering,2001,25(7):683-702.
[19]Pereira J M,Lerch B A.Effects of heat treatment on the ballistic impact properties of Inconel 718 for jet engine fan containment applications[J].International Journal of Impact Engineering,2001,25(8):715-733.
[20]Carney K S,Pereira J M,Revilock D M,et al.Jet engine fan blade containment using an alternate geometry[J].International Journal of Impact Engineering,2009,36:720-728.
[21]陈光涛,宣海军,刘璐璐,等.钛合金加筋板抗碎片冲击性能研究[J].兵工学报,2013,34(S1):220-224.CHEN Guangtao,XUAN Haijun,LIU Lulu,et al.Study on the ability to resist debris impact of titanium stiffened plate[J].Acta Armamentarii,2013,34(S1):220-224.(in Chinese)
[22]Zhang T,Chen W,Guan Y,et al.Study on titanium alloy TC4 ballistic penetration resistance Part I[J].Chinese Journal of Aeronautics,2012,25(3):388-395.
[23]Zhang T,Chen W,Guan Y,et al.Study on ballistic penetration resistance of titanium alloy TC4,Part II-numerical analysis[J].Chinese Journal of Aeronautics,2012,26(3):606-613.
[2]宣海军,陆晓,洪伟荣,等.航空发动机机匣包容性研究综述[J].航空动力学报,2010,25(8):1860-1870.XUAN Haijun,LU Xiao,HONG Weirong,et al.Review of aero-engine case containment research[J].Journal of Aerospace Power,2010,25(8):1860-1870.(in Chinese)
[3]马艳红,梁智超,王桂华,等.航空发动机叶片丢失问题研究综述[J].航空动力学报,2016(3):513-526.MA Yanhong,LIANG Zhichao,WANG Guihua,et al.Review on the blade loss of aero-engine[J].Journal of Aerospace Power,2016(3):513-526.(in Chinese)
[4]FAR33 Airworthiness standards:Aircraft engines[S].United States:Federal Aviation Administration,1984.
[5]中国民用航空总局.CCAR-33航空发动机适航规定[S].北京:中国民用航空总局,2005:78-79.Civil Aviation Administration of China.CCAR-33 Aviation engine airworthiness regulation[S].Beijing:Civil Aviation Administration of China,2005:78-79.(in Chinese)
[6]国防科学技术工业委员会.GJB 3366航空涡轮发动机包容性要求[S].北京:国防科学技术工业委员会,1998:1-3.Commission of Science.Technology and Industry for National Defense.GJB 3366 The requirements of aircraft turbine engine containment[S].Beijing:Commission of Science.Technology and Industry for National Defense,1998:1-3.(in Chinese)
[7]Xuan H,Wu R.Aeroengine turbine blade containment tests using high-speed rotor spin testing facility[J].Aerospace Science and Technology,2006,10(6):501-508.
[8]He Q,Xuan H,Liu L,et al.Perforation of aero-engine fan casing by a single rotating blade[J].Aerospace Science and Technology,2013,25(1):234-241.
[9]He Q,Xie Z,Xuan H,et al.Multi-blade effects on aero-engine blade containment[J].Aerospace Science and Technology,2016.49:101-111.
[10]Teng X,Wierzbicki T.Gouging and fracture of engine containment structure under fragment impact[J].Journal of Aerospace Engineering,2008,21(3):174-186.
[11]Kraus A,Frischbier J.Containment and penetration in case of blade loss in a low pressure turbine[C]//DYNAmore LS-DYNA Forum.Bad Mergentheim,September,2002.
[12]He Q,Xuan H,Liao L,et al.,Simulation methodology development for rotating blade containment analysis[J].Journal of Zhejiang University-SCIENCE A,2012,13(4):239-259.
[13]Sarkar S,Atluri S N.Effects of multiple blade interaction on the containment of blade fragments during a rotor failure[J].Finite Elements in Analysis and Design,1996,23(2-4):211-223.
[14]Hermosilla U,Alcaraz J L,Aja A M.Blade impact simulation against turbine casings[C]//2004 ABAQUS Users’Conference,Boston,MAUSA,2004.
[15]于亚彬,陈伟.模型机匣/叶片的包容性数值分析[J].航空动力学报,2005,20(3):429-433.YU Yabin,CHEN Wei.Numerical analysis of the modeled blade/casing containment[J].Journal of Aerospace Power,2005,20(3):429-433.(in Chinese)
[16]于连超,陈伟,关玉璞,等.多层机匣的包容性数值仿真研究[J].航空发动机,2009,35(4):32-35.YU Lianchao,CHEN Wei,GUAN Yupu,et al.Numerical simulation of multiplelayer casing containment[J].Aeroengine,2009,35(4):32-35.(in Chinese)
[17]Ambur D R,Jaunky N,Lawson R E,et al.A gas actuated projectile launcher for high energy impact testing of structure[R].A-IAA-99-1385.
[18]Ambur D R,Jaunky N,Lawson R E,et al.Numerical simulations for high-energy impact of thin plates[J].International Journal of Impact Engineering,2001,25(7):683-702.
[19]Pereira J M,Lerch B A.Effects of heat treatment on the ballistic impact properties of Inconel 718 for jet engine fan containment applications[J].International Journal of Impact Engineering,2001,25(8):715-733.
[20]Carney K S,Pereira J M,Revilock D M,et al.Jet engine fan blade containment using an alternate geometry[J].International Journal of Impact Engineering,2009,36:720-728.
[21]陈光涛,宣海军,刘璐璐,等.钛合金加筋板抗碎片冲击性能研究[J].兵工学报,2013,34(S1):220-224.CHEN Guangtao,XUAN Haijun,LIU Lulu,et al.Study on the ability to resist debris impact of titanium stiffened plate[J].Acta Armamentarii,2013,34(S1):220-224.(in Chinese)
[22]Zhang T,Chen W,Guan Y,et al.Study on titanium alloy TC4 ballistic penetration resistance Part I[J].Chinese Journal of Aeronautics,2012,25(3):388-395.
[23]Zhang T,Chen W,Guan Y,et al.Study on ballistic penetration resistance of titanium alloy TC4,Part II-numerical analysis[J].Chinese Journal of Aeronautics,2012,26(3):606-613.