涡轮盘热力耦合及中心孔疲劳裂纹扩展研究
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摘要
基于有限元软件ABAQUS/Franc3D,对某型航空发动机涡轮盘在热-机械载荷作用下的疲劳裂纹扩展规律进行研究。首先,进行涡轮盘网格无关性验证以保证计算精度;其次,针对涡轮盘进行导热分析以确定温度分布;再次开展了热-力载荷联合作用下的应力应变计算、静强度校核;最后,计算了中心孔处疲劳裂纹扩展参量以及疲劳裂纹扩展寿命。研究结果表明:该涡轮盘在最大转速状态下静强度满足要求,中心孔区域为应力集中危险点。裂纹尖端温度变化速率随着裂纹的深入而增加,导致了裂纹尖端应力场的扰动,裂纹由I型模式转为I/II混合模式。疲劳裂纹扩展寿命预测结果偏于危险,但可为涡轮盘损伤容限设计提供依据。
Based on the finite element software ABAQUS/Franc3 D, the stress and fatigue crack growth of an Aero-Engine Turbine Disk were investigated. Firstly, grid-independent verification was performed to ensure calculation accuracy. Secondly, the thermal conductivity of the turbine disk was simulated to determine the temperature distribution. Then, the stress-strain calculation and static strength checking were carried out under the condition of coupled thermal-mechanical loads. Finally, the fatigue crack growth parameters and fatigue crack growth life at the center hole were calculated. The results show that the static strength of the turbine disk meets the requirements at the maximum rotational speed, and the central hole area is the dangerous point of stress concentration.The temperature change rate at the crack tip increased with the depth of the crack, which leads to the disturbance of the stress field at the crack tip, and the crack changes from mode I to mode I/II. The fatigue crack growth life prediction results are dangerous, but it can provide a basis for damage tolerance design of turbine disk.
Based on the finite element software ABAQUS/Franc3 D, the stress and fatigue crack growth of an Aero-Engine Turbine Disk were investigated. Firstly, grid-independent verification was performed to ensure calculation accuracy. Secondly, the thermal conductivity of the turbine disk was simulated to determine the temperature distribution. Then, the stress-strain calculation and static strength checking were carried out under the condition of coupled thermal-mechanical loads. Finally, the fatigue crack growth parameters and fatigue crack growth life at the center hole were calculated. The results show that the static strength of the turbine disk meets the requirements at the maximum rotational speed, and the central hole area is the dangerous point of stress concentration.The temperature change rate at the crack tip increased with the depth of the crack, which leads to the disturbance of the stress field at the crack tip, and the crack changes from mode I to mode I/II. The fatigue crack growth life prediction results are dangerous, but it can provide a basis for damage tolerance design of turbine disk.
引文
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[2]Kogenhop O. Propagation lifetime calculation of the P&W compressor fan disc Life prediction based on crack growth[M]. America:National Lucht-en Ruimtevaart laboratorium,2000:200-302.
[3]Pokrvskii V V,Sidyachenko V G,Ezhov V N,et al. Basics of operation of GTE disks by the technical condition:the way to extend their design service life[J]. Strength of Meterials,2016,48(3):1–8.
[4]张智轩,石多奇,杨晓光.含销钉孔边裂纹的某压气机轮盘裂纹扩展分析[J].航空动力学报,2016,31(3):567–574.
[5]秦银雷,魏大盛,王延荣.航空发动机涡轮盘裂纹扩展分析[J].航空发动机,2010,36(2):35–38.
[6]Irwin G R. Analysis of stresses and strain near the end of a crack traversing a plate[J]. Journal of Applied Mechanics,1957,3(2):61–364.
[7]Neville D J,Knott J F. Statistical distributions of toughness and fracture stress for homogeneous and inhomogeneous materials[J].Journal of the Mechanics&Physics of Solids,1986,34(3):243–291.
[8]杨保华.航空发动机设计用材料数据手册第4册[M].北京:航空工业出版社,2010:200-205.
[9]陈勇.含夹杂粉末高温合金涡轮盘裂纹扩展寿命研究[D].南京:南京航空航天大学,2003:25-31.
[10]Arne M. A finite element study of short cracks with different inclusion types under rolling contact fatigue load[J]. International Journal of Fatigue,1997,19(1):13–24.
[11]陈雪松,李一红,唐文庆.复杂应力状态下20 g材料热机械疲劳试验研究[J].科技创新导报,2012(13):2–4.
[12]Tinga T. Aerospace lifing methods,specifically for gas turbines,National Aerospace Laboratory NLR[M]. The Netherlands:November1998:145-149.
[13]付娜.某航空发动机涡轮盘和叶片强度分析和寿命计算[D].西安:西北工业大学,2006.
[14]Daid N,Hills D A. Simulation of the growth of near-surface defects[J]. Engineering Fracture Mechanics,1998,59(4):415–424.
[15]Heo S P,Yang W H,Kim C. Stress intensity factors for elliptical arc through cracks in mechanical joints by virtual crack closure technique[J]. Ksme International Journal,2002,16(2):182–191.
[16]Kolkman H J. Discussion of the PWA lifing concept for the F100 engine-CIP task 463-,national aerospace laboratory NLR[M]. The Netherlands,1996:256-257.
[17]Cornell. FRANC3D reference manual[R]. New York:Version 7.0,Fracture Analysis Consultants Incorporation,2015:12-15.
[18]吕文林.航空涡喷、涡扇发动机结构设计准则第2册[R].北京:中国航空工业总公司发动机系统工程局,1997:457-489.
[19]宋兆泓,陈光,张景武,等.航空发动机典型故障分析[M].北京:北京航空航天大学出版社,1993:128-158.
[20]胡殿印,王荣桥,邓俊.基于有限元方法的裂纹扩展寿命预测[J].机械强度,2009,31(2):264–268.
[21]杨广里.断裂力学及应用[M].北京:国防工业出版社,1991:187-199.