ASTM E Waterhouse 6 1 Dobromirski 7 Suresh 3 50 Hertz SDS TC11 2 TC Tomlison 4 SDS50 Szolwinski Farris 4 4

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1 Mechanical Science and Technology for Aerospace Engineering March Vol No. 3 TC11 石炜, 温卫东, 崔海涛以航空发动机榫连接结构微动疲劳问题的简化模型为研究对象, 设计和制造了一套采用液压加载方式来实现微动疲劳法向载荷施加的试验装置, 用于研究钛合金 TC11 微动疲劳的损伤过程, 并对试验过程中在接触区域萌生裂纹的试件断口进行观测研究结果表明 : 保持法向载荷恒定不变, 增加轴向载荷将减少微动疲劳寿命同样, 保持轴向载荷恒定不变, 法向载荷对微动疲劳寿命影响不如轴向载荷显著另外, 等效应力和滑移幅值是微动疲劳寿命的主要影响因素微动损伤 ; 试验装置 ; 微动疲劳寿命 ; 轴向载荷 ; 法向载荷 V233 A Exploring Fretting Fatigue Behavior of TC11 Shi Wei Wen Weidong Cui Haitao College of Energy and Power Engineering Nanjing University of Aeronautics and Astronautics Nanjing Abstract The simplified model of the fretting fatigue of dovetail joints between the blade of an aero-engine and its disk was studied. An apparatus for fretting fatigue test was used to characterize the fretting fatigue damage process for titanium alloy TC11 and to observe the crack of the fracture specimen which is initiated in and around the contact zone during the test. The test results show that the number of crack initiation cycles decreases with an increase in the axial force that keeps normal force at a constant value. Also the influence of the normal force on the crack initiation cycle is not obvious because of the influence of the axial force. In addition the von Mises equivalent stress and the slip amplitude are the main causes for the reduction of the number of crack initiation cycles. Key words aircraft engines axial force crack initiation cycles crack initiation disks structural components experiments fatigue damage fatigue of materials fretting damage normal force test apparatus titanium alloys turbomachine blades % TC nuaashiwei@ nuaa. edu. cn gswwd@ nuaa. edu. cn TC11 1 1

2 ASTM E Waterhouse 6 1 Dobromirski 7 Suresh 3 50 Hertz SDS TC11 2 TC Tomlison 4 SDS50 Szolwinski Farris 4 4

3 TC11 449 130. 90 MPa 229. 07 MPa 10 1 1 TC11 4 TC - 3 65. 45 400 0. 1 25 065 TC - 4 98. 17 400 0. 1 15 322 TC - 5 130. 90 200 0. 1 109 307 2. 2 TC 8-6 130. 90 300 0. 1 24 989 TC - 7 130. 90 400 0.

3 3 TC MPa MPa TC11 4 TC TC TC TC TC GBT TC TC TC ~ 2 mm TC TC11 TC11 TC11 = 540 MPa σ b = 9 σ MPa σ s = 866 MPa E = 120 GPa μ = /MPa /MPa TC TC / TC mm MPa 300 MPa 400 MPa MPa MPa 7

4 TC11 S-N MPa 200 MPa 300 MPa % 300 MPa 400 MPa 3. 60% MPa 200 MPa 300 MPa % 300 MPa 400 MPa % MPa 300 MPa 400 MPa % MPa 400 MPa 300 MPa MPa MPa MPa % MPa S-N MPa MPa % MPa MPa 5. 69% MPa MPa MPa MPa MPa % MPa y = Ax - m MPa % 9 ~ 11 TC11 TC TC11 Walker σ eq = σ max 1 - R m TC11

5 3 TC ~ 11 1 Léo Vincent. M Zhou Z R Léo Vincent. Fretting wear M. Beijing Science Press 2002 in Chinese 2. M He M J. Fretting fatigue of mechanical component M. Beijing National Defence Industry Press 1994 in Chinese 3 Suresh S. M Suresh S. Fatigue of Materials M. Wang Z G. 2nd Beijing National Defence Industry Press 1999 in Chinese 10 TC11 4 Szolwinski M P Farris T N. Observation analysis and prediction of fretting fatigue in 2024-T351 aluminum alloy J. Wear ASTM E Standard guide for fretting fatigue testing S. West Conshohocken Pennsylvania ASTM International DOI /C < www. astm. org > 6 Waterhouse R B. The problems of fretting fatigue testing C / / Standardization of Fretting Fatigue Test Methods and Equipment. ASTM STP 1159 Philadelphia American Society for Testing and Materials 11 TC Dobromirski J M. Variables of fretting process are there 4 50 of them C / /Standardization of Fretting Fatigue Test Methods and Equipment ASTM STP 1159 Philadelphia American Society of Testing and Materials D TC11 Gu Y X. Research on fretting fatigue life of dovetail joint under HCF-LCF load D. Nanjing Nanjing University 2 of Aeronautics and Astronautics 2007 in Chinese 9 Fadag H A Mall S Jain V K. A finite element analysis of fretting fatigue crack growth behavior in Ti-6Al-4V J. Engineering Fracture Mechanics S The Editorial Board of China Aeronautical Materials 4 Handbook. China aeronautical materials handbook volume 4 titanium alloy copper alloy S. Beijing China Standards Press 2001 in Chinese

76 34 2. 1. 1 Fig. 1 1 a-a b-b a-a σ ma = 74. 4 MPa σ a = 15. 74 MPa σ 0a =90. 15 MPa 0. 9 σ t =135 MPa b-b σ mb = 21. 77 MPa τ b = 13. 789 MPa σ 0b =

76 34 2. 1. 1 Fig. 1 1 a-a b-b a-a σ ma = 74. 4 MPa σ a = 15. 74 MPa σ 0a =90. 15 MPa 0. 9 σ t =135 MPa b-b σ mb = 21. 77 MPa τ b = 13. 789 MPa σ 0b = 34 11 2012 11 SHIP SCIENCE AND TECHNOLOGY Vol. 34 No. 11 Nov. 2012 0 430064 GB150-98 ASME THR3 +. 4 A 1672-7649 2012 11-0075 - 07 doi 10. 3404 /j. issn. 1672-7649. 2012. 11. 017 Stress and fatigue analysis