Effects of Hot Rolling on Low-Cycle Fatigue Properties of Zn-22 wt.% Al Alloy at Room Temperature

2016 ◽  
Vol 25 (9) ◽  
pp. 3822-3829 ◽  
Author(s):  
X. H. Dong ◽  
Q. D. Cao ◽  
S. J. Ma ◽  
S. H. Han ◽  
W. Tang ◽  
...  
Keyword(s):  
Hot Rolling ◽  
Room Temperature ◽  
Low Cycle Fatigue ◽  
Fatigue Properties ◽  
Al Alloy ◽  
Cycle Fatigue

scholarly journals Low Cycle Fatigue Properties of Alloy 617 base Metal and Weld Joint at Room Temperature

2014 ◽  
Vol 3 ◽  
pp. 2201-2206 ◽  
Author(s):  
Seon-Jin Kim ◽  
Pil-Ho Choi ◽  
Rando Tungga Dewa ◽  
Woo-Gon Kim ◽  
Min-Hwan Kim
Keyword(s):  
Base Metal ◽  
Weld Joint ◽  
Room Temperature ◽  
Low Cycle Fatigue ◽  
Fatigue Properties ◽  
Cycle Fatigue ◽  
Alloy 617

High-Temperature Fatigue Properties of Single Crystal Superalloys in Air and Hydrogen

2004 ◽  
Vol 126 (3) ◽  
pp. 590-603 ◽  
Author(s):  
N. K. Arakere
Keyword(s):  
Fatigue Life ◽  
Single Crystal ◽  
Room Temperature ◽  
Low Cycle Fatigue ◽  
Turbine Blades ◽  
Fatigue Properties ◽  
Cycle Fatigue ◽  
Fatigue Data ◽  
Blade Tip ◽  
Pressure Hydrogen

Hot section components in high-performance aircraft and rocket engines are increasingly being made of single crystal nickel superalloys such as PWA1480, PWA1484, CMSX-4, and Rene N-4 as these materials provide superior creep, stress rupture, melt resistance, and thermomechanical fatigue capabilities over their polycrystalline counterparts. Fatigue failures in PWA1480 single crystal nickel-base superalloy turbine blades used in the space shuttle main engine fuel turbopump are discussed. During testing many turbine blades experienced stage II noncrystallographic fatigue cracks with multiple origins at the core leading edge radius and extending down the airfoil span along the core surface. The longer cracks transitioned from stage II fatigue to crystallographic stage I fatigue propagation, on octahedral planes. An investigation of crack depths on the population of blades as a function of secondary crystallographic orientation (β) revealed that for β=45+/−15 deg tip cracks arrested after some growth or did not initiate at all. Finite element analysis of stress response at the blade tip, as a function of primary and secondary crystal orientation, revealed that there are preferential β orientations for which crack growth is minimized at the blade tip. To assess blade fatigue life and durability extensive testing of uniaxial single crystal specimens with different orientations has been tested over a wide temperature range in air and hydrogen. A detailed analysis of the experimentally determined low cycle fatigue properties for PWA1480 and SC 7-14-6 single crystal materials as a function of specimen crystallographic orientation is presented at high temperature (75°F–1800°F) in high-pressure hydrogen and air. Fatigue failure parameters are investigated for low cycle fatigue data of single crystal material based on the shear stress amplitudes on the 24 octahedral and 6 cube slip systems for FCC single crystals. The max shear stress amplitude [Δτmax] on the slip planes reduces the scatter in the low cycle fatigue data and is found to be a good fatigue damage parameter, especially at elevated temperatures. The parameter Δτmax did not characterize the room temperature low cycle fatigue data in high-pressure hydrogen well because of the noncrystallographic eutectic failure mechanism activated by hydrogen at room temperature. Fatigue life equations are developed for various temperature ranges and environmental conditions based on power-law curve fits of the failure parameter with low cycle fatigue test data. These curve fits can be used for assessing blade fatigue life.

Low Cycle Fatigue Evaluation of Inconel 713C and Waspaloy

1965 ◽  
Vol 87 (2) ◽  
pp. 275-289 ◽  
Author(s):  
JoDean Morrow ◽  
F. R. Tuler
Keyword(s):  
Fatigue Life ◽  
Plastic Strain ◽  
Strain Energy ◽  
Room Temperature ◽  
Low Cycle Fatigue ◽  
Fatigue Properties ◽  
Cycle Fatigue ◽  
Plastic Strain Energy ◽  
Fatigue Evaluation ◽  
Inconel 713C

Completely reversed axial fatigue results are reported for Waspaloy and Inconel 713C at room temperature. Fatigue strength and ductility are evaluated using power functions of the fatigue life. The exponents and coefficients of these two equations are looked upon as four fatigue properties of the material. They appear in the equations which are developed to relate cyclic stress, plastic strain, total strain, plastic strain energy per cycle, total plastic strain energy to fracture, and fatigue life. These equations and the four fatigue properties permit the evaluation of the relative fatigue resistance of various metals at different fatigue lives when subjected to strain, stress, or plastic strain energy cycling. The “best” selection of material to resist fatigue is found to depend on the type of cycling and the desired life. At room temperature, the wrought Waspaloy is found to be more fatigue resistant than the cast Inconel 713C, particularly in resisting strain or plastic strain energy cycling in the low cycle fatigue region. For longer lives the difference in fatigue resistance between the two diminishes, especially for stress cycling. It is believed that the method of fatigue evaluation used here is generally applicable to the engineering problem of material selection to resist fatigue, and should in some cases replace methods based on conventional rotating bending fatigue tests which only evaluate the fatigue strength at long lives.

Low cycle fatigue properties and microstructure of P92 ferritic-martensitic steel at room temperature and 873 K

2019 ◽  
Vol 157 ◽  
pp. 109923 ◽  
Author(s):  
Zhen Zhang ◽  
Zhengfei Hu ◽  
Siegfried Schmauder ◽  
Baosen Zhang ◽  
Zhangzhong Wang
Keyword(s):  
Room Temperature ◽  
Martensitic Steel ◽  
Low Cycle Fatigue ◽  
Fatigue Properties ◽  
Cycle Fatigue

Shot Peening Effect on Low Cycle Fatigue Properties of Ti-6Al-4V and Inconel 718

2011 ◽  
Author(s):  
Hiroshi Nakamura ◽  
Masahiro Takanashi ◽  
Yu Itabashi ◽  
Hiroshi Kuroki ◽  
Yusuke Ueda
Keyword(s):  
Residual Stress ◽  
Shot Peening ◽  
Inconel 718 ◽  
Room Temperature ◽  
Low Cycle Fatigue ◽  
Strain Range ◽  
Fatigue Tests ◽  
Fatigue Properties ◽  
Cycle Fatigue ◽  
Polished Specimen

This study investigates the shot peening effect on low cycle fatigue properties of two turbo engine materials, Ti-6Al-4V and Inconel 718, in view of the residual stress relaxation by the cyclic load and the thermal relaxation. Strain controlled fatigue tests for Ti-6Al-4V were carried out at room temperature. The fatigue tests for Inconel 718 were conducted at room temperature and 620C. An X-ray diffraction method was used to measure the residual stresses induced by shot peening. The compressive residual stress of Ti-6Al-4V specimen had retained about 60% after half the number of cycles to failure. It is confirmed that shot peening enhances strain range capability of Ti-6Al-4V at the life between 104 and 105 cycles region about 1.5 times higher than that of non-peened specimen. This result is attributed to the retained compressive layer even after applied cyclic loading. Shot peening enhanced the strain range capability of the Inconel 718 specimen at room temperature, by a factor of 1.3 compared to polished specimen at the life of 104 cycles region. The residual stress near the surface has been relaxed rapidly at turbine engine temperature, however, the residual stresses in the deep subsurface have been retained. The peened specimen tested at 620C tended to be slightly higher strain range than those of polished specimen at the life of 105 cycles.

scholarly journals Low-cycle fatigue properties of ultrafine-grained zinc–22 wt.% aluminum alloy during room-temperature superplastic flow

2008 ◽  
Vol 59 (2) ◽  
pp. 215-218 ◽  
Author(s):  
Tsutomu Tanaka ◽  
Atsumichi Kushibe ◽  
Masahide Kohzu ◽  
Yorinobu Takigawa ◽  
Kenji Higashi
Keyword(s):  
Aluminum Alloy ◽  
Room Temperature ◽  
Low Cycle Fatigue ◽  
Superplastic Flow ◽  
Fatigue Properties ◽  
Cycle Fatigue ◽  
Ultrafine Grained

Effects of Modified Solution Heat Treatment on δ- Phase and Low Cycle Fatigue Properties of Inconel 718 Alloy

2006 ◽  
Vol 118 ◽  
pp. 71-76 ◽  
Author(s):  
Jae Keun Hong ◽  
Ji Hong Park ◽  
Nho Kwang Park ◽  
Seong Jun Kim ◽  
Chung Yun Kang
Keyword(s):  
Heat Treatment ◽  
Solution Heat Treatment ◽  
Room Temperature ◽  
Low Cycle Fatigue ◽  
Fatigue Tests ◽  
Fatigue Properties ◽  
Alloy 718 ◽  
Cycle Fatigue ◽  
Standard Heat ◽  
Heat Treated

Effects of solution treatment on the microstructure and mechanical properties in wrought Alloy 718 were investigated. For the improvement of tensile and fatigue properties of wrought Alloy 718, a modified solution heat treatment(MSHT), heating at 1000 for 3 minutes followed by furnace cooling at the rate of 3/minute and holding at 985 for 8 minutes, was proposed. This treatment was performed repeatedly 3 times and the samples were subject to the standard aging treatment. For the purpose of comparison, a standard heat treatment(SHT) was also performed. The microstructures of modified solution heat treated specimens showed that small spherical shaped δ- phases were precipitated without grain growth, and the amount of δ-phases was smaller than that of standard heat treated specimens. However, the δ-phases of the standard heat-treated specimen showed needle-like morphologies. Tensile and low cycle fatigue tests were performed on both modified heat-treated and standard heat-treated specimens at room temperature, 350 and 650. Low cycle fatigue tests on the modified heat treated specimens showed promising results without reduction of strength. However, the tensile properties of modified solution treated specimens was almost the same as those of standard heat treated materials both at room temperature and 650.

Fatigue Properties of 316L Stainless Steel

2012 ◽  
Vol 204-208 ◽  
pp. 3786-3789
Author(s):  
Xiao Zhao
Keyword(s):  
Stainless Steel ◽  
Room Temperature ◽  
316L Stainless Steel ◽  
Low Cycle Fatigue ◽  
Fatigue Cracks ◽  
Testing Machine ◽  
Experimental Studies ◽  
Hydraulic Testing ◽  
Fatigue Properties ◽  
Cycle Fatigue

The present paper deals with experimental studies on the tension-tension fatigue properties of 316L stainless steel by using a servo-valve controlled electro-hydraulic testing machine at room temperature. The low cycle fatigue properties of 316L stainless steel were studied and the initiation mechanisms of fatigue cracks were investigated and analyzed with scanning electron microscopy (SEM). Preliminary results indicate that the S-N curve of 316L stainless steel descends linearly in the low cycle regime and fatigue failure initiates from inclusions/defects on the specimen surface.

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