航空发动机空气涡轮起动机包容结构研究
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摘要
为了解某航空发动机空气涡轮起动机包容结构对其包容性的影响,采用LS-DYNA软件对空气涡轮起动机的包容性进行数值仿真,并在高速旋转试验台上开展了多次包容性试验。试验中采用涡轮盘预制裂纹的方式,使涡轮均匀破裂成3块,针对不同厚度的包容结构和不同的包容环支承结构分别进行包容试验。试验结果表明:在厚壁包容结构试验中轮盘碎块飞出,包容效果不理想;在薄壁包容结构试验中轮盘碎块击穿内层壳体并撞击包容环,轮盘碎块无飞出,包容效果较为理想;在薄壁包容结构试验中采用螺钉固定支承结构,第1次试验成功包容,第2次试验中涡轮盘被包容但组件倒翻,在第3次试验中采用凸台加固支承结构成功包容,表明选用合适的包容结构及其支承结构对确保其具备有效的包容能力十分重要。研究结果对空气涡轮起动机的包容结构设计有很好的指导意义。
In order to understand the influence of the containment structure of an aeroengine air turbine starter on its inclusiveness,the numerical simulation of the inclusiveness of the air turbine starter was carried out by using the software of LS-DYNA. Several inclusiveness tests were carried out on a high-speed rotating test-bed. In the tests,the turbine was cracked evenly into three pieces by the way of prefabricating cracks on the turbine disk. The containment tests were carried out for the containment structures with different thickness and the supporting structures with different supporting rings. The experimental results show that in the test of thick wall containment structure,the turbine disk fragments fly out and the containment effect is not satisfactory. In the test of thin wall containment structure,the turbine disk fragments break through the shell of the inner layer and impact the containment ring,the turbine disk fragments do not fly out and the containment effect is satisfactory. The screw-fixed support structure is adopted in the test of thin wall containment structure and the first test is successful. In the second test,the turbine disk is contained but the module turns over. In the third test,the support structure strengthened by convex abutment is successful. It is shown that it is very important to select suitable containment structures and supporting structures to ensure that it has effective containment ability. The study results have great significance for the design of containment structure of the air turbine starters.
In order to understand the influence of the containment structure of an aeroengine air turbine starter on its inclusiveness,the numerical simulation of the inclusiveness of the air turbine starter was carried out by using the software of LS-DYNA. Several inclusiveness tests were carried out on a high-speed rotating test-bed. In the tests,the turbine was cracked evenly into three pieces by the way of prefabricating cracks on the turbine disk. The containment tests were carried out for the containment structures with different thickness and the supporting structures with different supporting rings. The experimental results show that in the test of thick wall containment structure,the turbine disk fragments fly out and the containment effect is not satisfactory. In the test of thin wall containment structure,the turbine disk fragments break through the shell of the inner layer and impact the containment ring,the turbine disk fragments do not fly out and the containment effect is satisfactory. The screw-fixed support structure is adopted in the test of thin wall containment structure and the first test is successful. In the second test,the turbine disk is contained but the module turns over. In the third test,the support structure strengthened by convex abutment is successful. It is shown that it is very important to select suitable containment structures and supporting structures to ensure that it has effective containment ability. The study results have great significance for the design of containment structure of the air turbine starters.
引文
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[22] Deya S,Brovik T,Hopperstada O S,et al. On the influence of constitutive relation in projectile impact of steel plates[J]. International Journal of Impact Engineering,2007(34):464-486.
[23] Teng X Wierzbicki T. Evaluation of six fracture models in high velocity perforation[J]. Engineering Fracture Mechanics,2006(73):1653-1678.
[24]中国航空材料手册编辑委员会.中国航空材料手册:第3卷铝合金镁合金[M].第2版.北京:中国标准出版社,2002:383-393.China Aviation Materials Manual Editorial Board. Aerospace materials manual of China(vol. 3):aluminum and magnesium alloys[M].2nd ed.Beijing:China Standard Press,2002.:383-393.
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[2]张伯熹,宣海军,吴荣仁.航空发动机涡轮叶片包容模拟实验研究[J].机械工程师,2006(10):114-116.ZHANG Boxi,XUAN Haijun,WU Rongren. Research on aero-engine turbine blade containment experiment[J]. Mechical Engineer,2006(10):114-116.
[3]宣海军,何泽侃,牛丹丹,等.航空发动机软壁风扇机匣包容性研究[J].航空发动机,2015,41(6):81-87.XUAN Haijun,HE Zekan,NIU Dandan,et al. Investigation on containment of aeroengine soft-wall fan case[J]. Aeroengine,2015,41(6):81-87.
[4]何泽侃,宣海军,胡燕琪,等. Kevlar缠绕增强机匣包容过程研究[J].工程力学,2017,34(S1):308-313.HE Zekan,XUAN Haijun,HU Yanqi,et al. Investigation on containment process of case wrapped with kevlar fabric[J]. Engineering Mechanics,2017,34(S1):308-313.
[5] Naik D,Sankaran S,Mobasher B,et al. Development of reliable modeling methodologies f or fan blade out containment analysis,partⅠ:experimental studies[J]. International Journal of Impact Engineering,2009,36:1-11.
[6] Stahlecker Z,Mobasher B,Rajan S D,et al. Development of reliable modeling methodologies f or engine fan blade out containment analysis,part II:f inite element analysis[J].International Journal of Impact Engineering,2009,36:447-459.
[7] Xuan H J,Wu R R. Aero-engine turbine blade containment tests using high-speed rotor spin testing facility[J]. Aerospace Science and Technology,2006(10):501-508.
[8]刘璐璐,宣海军,张娜,等.某涡轮冷却器压气机轮盘包容性研究[C]∥第22届全国结构工程学术会议论文集.乌鲁木齐:工程力学杂志出版社,2013:190-195.LIU Lulu,XUAN Haijun,ZHANG Na,et al. Research on compressor disc containment of a cooling turbine[C]//Proceedings of the 22nd national conference on structural engineering. Urumqi:Journal of Engineering Mechanics Press,2013:190-195.
[9]李娟娟,宣海军,廖连芳.轮盘碎片撞击圆筒体的实验研究[J].兵工学报,2009,30(S2):218-222.LI Juanjuan,XUAN Haijun,LIAO Lianfang. Experimental study of cylindrical case impacted by disk fragments[J]. Acta Armamentarii,2009,30(S2):218-222.
[10] Li J J,Xuan H J,Liao L F,et al. Penetration of disk fragments following impact on thin plate[J]. Journal of Zhejiang University:Science A,2009,10(5):677-684.
[11] Xuan H J,Liu J L,Feng Y M,et al. Containment of high-speed rotating disk fragments[J]. Journal of Zhejiang University:Science A,2012,13(9):665-673.
[12]唐金,唐广,宣海军,等.航空发动机涡轮机匣轮盘包容性研究[J].航空动力学报,2016,31(6):1393-1399.TANG Jin,TANG Guang,XUAN Haijun,et al. Investigation on disk containment of aero-engine turbine casing[J]. Journal of Aerospace Power. 2016,31(6):1393-1399.
[13] Stamper E,Hals S. The use of LS-DYNA model to predict containment of disk burst fragments[C]//Proceedings of 10th International LS-DYNA Users Conference.Dearborn,Michigan,USA:Livermore Software Technology Corporation,2008:9-25.
[14] Hagg A C,Sankey G O. The containment of disk burst fragment bycylindrical shells[J]. Journal of Engineering for Gas Turbines&Power,1974,96(2):114.
[15] Harding J. The development of constitutive relationships for material behaviour at high rates of strain[J]. Institute of Physics Conference Series,1989(102):189-202.
[16] Zukas J A,Hohler V,Jameson R L,et al. High velocity impact dynamics[M]. New York:Wiley,1990:93-708.
[17] Liang R,Khan A S. A critical review of experimental results and constitutive models for BCC and FCC metals over a wide range of strain rates and temperatures[J]. International Journal of Plasticity,1999(15):963-980.
[18] Johnson G R,Cook W H. A constitutive model and data for metals subjected to large strains,high strain rates and high temperatures[C]//Proceedings of the seventh international symposium on ballistics.The Hague,1983,541-547.
[19] Zerilli F J,Armstrong R W. Dislocation-mechanics-based constitutive relations for material dynamics calculations[J]. Journal of Applied Physics,1987,61(5):1816-1825.
[20] Zerilli F J,Armstrong R W. Description of tantalum deformation behavior by dislocation mechanics based constitutive relations[J]. Journal of Applied Physics,1990,68(4):1580-1591.
[21] Zerilli F J,Armstrong R W. Dislocation mechanics based analysis of material dynamics behavior:enhanced ductility,deformation twinning, shock deformation, shear instability, dynamic recovery[J].Journal of Physics IV France,1997(7):637-642.
[22] Deya S,Brovik T,Hopperstada O S,et al. On the influence of constitutive relation in projectile impact of steel plates[J]. International Journal of Impact Engineering,2007(34):464-486.
[23] Teng X Wierzbicki T. Evaluation of six fracture models in high velocity perforation[J]. Engineering Fracture Mechanics,2006(73):1653-1678.
[24]中国航空材料手册编辑委员会.中国航空材料手册:第3卷铝合金镁合金[M].第2版.北京:中国标准出版社,2002:383-393.China Aviation Materials Manual Editorial Board. Aerospace materials manual of China(vol. 3):aluminum and magnesium alloys[M].2nd ed.Beijing:China Standard Press,2002.:383-393.
[25]中国航空材料手册编辑委员会.中国航空材料手册:第4卷钛合金铜合金[M].第2版.北京:中国标准出版社,2002:104-179.China Aviation Materials Manual Editorial Board. Aerospace materials manual of China(vol. 4):titanium and copper alloys[M]. 2nd ed.Beijing:China Standard Press,2002:104-179.