Effects of temperature and load on fretting fatigue induced geometrically necessary dislocation distribution in titanium alloy

2021 ◽  
Vol 800 ◽  
pp. 140308
Author(s):  
Qinan Han ◽  
Xusheng Lei ◽  
Hao Yang ◽  
Xiaolin Yang ◽  
Zimu Su ◽  
...  
Keyword(s):  
Titanium Alloy ◽  
Fretting Fatigue ◽  
Dislocation Distribution ◽  
Geometrically Necessary Dislocation ◽  
Effects Of Temperature

Application of FEM Modeling to Simulate Metal Flow in Forging a Titanium Alloy Engine Disk

1983 ◽  
Vol 105 (4) ◽  
pp. 251-258 ◽  
Author(s):  
S. I. Oh ◽  
J. J. Park ◽  
S. Kobayashi ◽  
T. Altan
Keyword(s):  
Finite Element Method ◽  
Finite Element ◽  
Titanium Alloy ◽  
Metal Flow ◽  
The Finite Element Method ◽  
Fem Modeling ◽  
Forging Process ◽  
Deformation Mechanics ◽  
Effects Of Temperature ◽  
Element Method

The isothermal forging of a titanium alloy engine disk is analyzed by the rigid-viscoplastic finite element method. Deformation mechanics of the forging process are discussed, based on the solution. The effects of temperature and heat conduction on the forging process are also investigated by coupled thermo-viscoplastic analysis. Since the dual microstructure / property titanium disk can be obtained by controlling strain distribution during forging, the process modeling by the finite element method is especially attractive.

S043022 Fretting fatigue properties of titanium alloy with CrN thin film

2011 ◽  
Vol 2011 (0) ◽  
pp. _S043022-1-_S043022-4
Author(s):  
Hiroshi MEISHIN ◽  
Shota TANIMOTO ◽  
Daisuke YONEKURA ◽  
Ri-chi MURAKAMI
Keyword(s):  
Thin Film ◽  
Titanium Alloy ◽  
Fretting Fatigue ◽  
Fatigue Properties

S0401-2-4 Fretting fatigue properties of titanium alloy with hard thin film.

2010 ◽  
Vol 2010.1 (0) ◽  
pp. 315-316
Author(s):  
Shota Tanimoto ◽  
Daisuke Yonekura ◽  
Ri-ichi Murakami
Keyword(s):  
Thin Film ◽  
Titanium Alloy ◽  
Fretting Fatigue ◽  
Fatigue Properties

scholarly journals Repair and Life Extension of Titanium Alloy Fan Blades in Aircraft Gas Turbines

1989 ◽  
Author(s):  
P. C. Patnaik ◽  
M. R. Pishva ◽  
J. E. Elder ◽  
W. Doswell ◽  
R. Thamburaj
Keyword(s):  
Titanium Alloy ◽  
Gas Turbines ◽  
Low Cycle Fatigue ◽  
Fretting Fatigue ◽  
Life Extension ◽  
Cycle Fatigue ◽  
Foreign Object Damage ◽  
Life Improvement ◽  
Qualification Testing ◽  
Non Destructive

Commercial and military aircraft gas turbine fan blades can suffer various types of damage in service, such as foreign object damage (FOD), high strain low cycle fatigue (LCF), wear and fretting fatigue. In addition, cracks initiated by one or more of these types of damage may propagate by a high cycle fatigue (HCF) mechanism. The component may therefore be life limited by the dominant failure mechanism. In this paper, a new, comprehensive scheme for economical refurbishment and qualification of service damaged titanium alloy fan blades is described, along with a critical review of the merits and demerits of existing repair schemes. The metallurgical and process variables to be considered in the repair of FOD, LCF life extension, wear and fretting fatigue life improvement are considered in detail with practical examples derived from experience. A complete qualification testing program including metallography, non-destructive inspection and mechanical property testing, for the refurbished component is outlined.

scholarly journals Effect of Laser Shock Peening on Fretting Fatigue Life of TC11 Titanium Alloy

Materials ◽  
2020 ◽  
Vol 13 (21) ◽  
pp. 4711
Author(s):  
Xufeng Yang ◽  
Hongjian Zhang ◽  
Haitao Cui ◽  
Changlong Wen
Keyword(s):  
Titanium Alloy ◽  
Fatigue Life ◽  
Power Density ◽  
Laser Power ◽  
Fretting Fatigue ◽  
Laser Power Density ◽  
Laser Shock Peening ◽  
Laser Shock ◽  
Shock Peening ◽  
Tc11 Titanium Alloy

The purpose of this paper is to investigate the performance of laser shock peening (LSP) subjected to fretting fatigue with TC11 titanium alloy specimens and pads. Three laser power densities (3.2 GW/cm2, 4.8 GW/cm2 and 6.4 GW/cm2) of LSP were chosen and tested using manufactured fretting fatigue apparatus. The experimental results show that the LSP surface treatment significantly improves the fretting fatigue lives of the fretting specimens, and the fretting fatigue life increases most when the laser power density is 4.8 GW/cm2. It is also found that with the increase of the laser power density, the fatigue crack initiation location tends to move from the surface to the interior of the specimen.

Evaluation of the Fretting Fatigue Behavior of Ti-6Al-4V Alloy

2005 ◽  
Vol 297-300 ◽  
pp. 1089-1094
Author(s):  
Jae Do Kwon ◽  
Yong Tak Bae ◽  
Sung Jong Choi ◽  
Young Suck Chai ◽  
Hitoshi Ishii
Keyword(s):  
Titanium Alloy ◽  
Fatigue Limit ◽  
Degradation Mechanism ◽  
Fatigue Behavior ◽  
Lamellar Microstructure ◽  
Fretting Fatigue ◽  
Mechanical Tests ◽  
Structural Components ◽  
Specific Strength ◽  
Fretting Damage

Fretting is a potential degradation mechanism of structural components and equipments exposed to various environments and loading conditions. It is well known that the fatigue life under fretting condition decreases approximately 50-70% compared with that under non-fretting fatigue condition. The specific gravity of titanium alloy is 4.5 which is lighter than steel, however, its specific strength, heat and corrosion resistance are superior to steel. Ti-6Al-4V alloy is a kind of a+b phase titanium alloy, and mechanical properties are changed by alloy elements, shapes and distributions of microstructures. In this study, three different kinds of specimens are prepared under different heat treatments in order to produce different microstructures. Through various kinds of mechanical tests, the following conclusions are observed: 1) The microstructures are observed as equiaxed, bimodal and lamellar microstructures respectively. 2) The elongation percentage is superior for the equiaxed microstructure, and the hardness and tensile strength are superior for the lamellar microstructure. 3) The plain fatigue limit of lamellar structure shows higher value than that of the equiaxed and bimodal structures. 4) The fretting fatigue limit considerably decreases compared with the plain fatigue limit for all materials. 5) The fretting damage of contact surface increases with an increase of cyclic loading amplitude under the constant contact pressure.

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