Fatigue Failure of Titanium Alloy Compressor Blades

1993 ◽  
pp. 299-300
Keyword(s):  
Titanium Alloy ◽  
Fatigue Failure ◽  
Compressor Blades

Investigation of tensile and high cycle fatigue failure behavior on a TIG welded titanium alloy

2021 ◽  
Vol 132 ◽  
pp. 107115
Author(s):  
Duqiang Ren ◽  
Yun Jiang ◽  
Xiaoan Hu ◽  
Xianzheng Zhang ◽  
Xiaoping Xiang ◽  
...  
Keyword(s):  
Titanium Alloy ◽  
Fatigue Failure ◽  
High Cycle Fatigue ◽  
Failure Behavior ◽  
Cycle Fatigue

Evaluating the parameters of spasmodic growth of a fatigue crack in compressor blades made of VT3-1 titanium alloy

1981 ◽  
Vol 17 (1) ◽  
pp. 65-68
Author(s):  
L. R. Botvina ◽  
L. V. Limar' ◽  
B. S. Logovikov
Keyword(s):  
Titanium Alloy ◽  
Fatigue Crack ◽  
Compressor Blades

Influence of Ultrafine-Grained Structure on the Kinetics and Fatigue Failure Mechanism of VT6 Titanium Alloy

2019 ◽  
Vol 60 (3) ◽  
pp. 253-258 ◽  
Author(s):  
G. V. Klevtsov ◽  
R. Z. Valiev ◽  
I. P. Semenova ◽  
N. A. Klevtsova ◽  
V. A. Danilov ◽  
...  
Keyword(s):  
Titanium Alloy ◽  
Failure Mechanism ◽  
Fatigue Failure ◽  
Ultrafine Grained Structure ◽  
Ultrafine Grained

Very High Cycle Fatigue Failure of Near β Titanium Alloy

2021 ◽  
Vol 24 (3) ◽  
pp. 326-334
Author(s):  
E. V. Naydenkin ◽  
A. P. Soldatenkov ◽  
I. P. Mishin ◽  
V. A. Oborin ◽  
A. A. Shanyavskiy
Keyword(s):  
Titanium Alloy ◽  
Fatigue Failure ◽  
High Cycle Fatigue ◽  
Cycle Fatigue ◽  
Very High Cycle Fatigue ◽  
Very High

Precision Forging Process Analysis and Preform Optimization of Small Compressor Blade of Titanium Alloy

2013 ◽  
Vol 364 ◽  
pp. 493-499 ◽  
Author(s):  
Wen Chen Xu ◽  
De Bin Shan ◽  
Wei Feng Zhang ◽  
Yan Lu
Keyword(s):  
Titanium Alloy ◽  
Process Analysis ◽  
Compressor Blade ◽  
Geometric Shape ◽  
Compressor Blades ◽  
Forging Process ◽  
Dimensional Precision ◽  
Precision Forging ◽  
Preheating Temperature ◽  
Preform Optimization

Small compressor blades of titanium alloy are important mechanical structural components of advanced aircraft engines. In the present study, the preheating scheme and the forging process of the small compressor blade were modeled by the commercial software DEFORM3D and the forging experiments were conducted on a 10,000KN screw press. The results show that the reasonable preheating temperature for the small blade should be controlled in 960-970°C. The geometric shape and size of the blade preform influenced not only overlap and underfilling defects but also the dimensional precision of small compressor blade forgings. On this basis, the optimized geometric shape of the blade preform was obtained and the compressor blades were well formed by limited forging process experiments.

scholarly journals Influence of Welded Pores on Very Long-Life Fatigue Failure of the Electron Beam Welding Joint of TC17 Titanium Alloy

Materials ◽  
2019 ◽  
Vol 12 (11) ◽  
pp. 1825 ◽  
Author(s):  
Fulin Liu ◽  
Hong Zhang ◽  
Hanqing Liu ◽  
Yao Chen ◽  
Khan Muhammad Kashif ◽  
...  
Keyword(s):  
Titanium Alloy ◽  
Electron Beam ◽  
Fatigue Life ◽  
Base Metal ◽  
Fatigue Failure ◽  
Electron Beam Welding ◽  
Welded Joint ◽  
Fatigue Cracks ◽  
Failure Behavior ◽  
Long Life

The electron beam welding process is widely used in the connection among titanium alloy material parts of aero-engines. Its mechanical properties need to meet the requirements of long life and high reliability. In this paper, the static strength and the fatigue failure behavior of the electron beam weldments of TC17 titanium alloy were investigated experimentally under low amplitude high frequency (20 kHz), and the mechanical response and failure mechanism under different external loading conditions were analyzed. In summary, the samples were found to have anisotropic microstructure. The tensile strength of the PWHT of TC17 EBW joint was ~4.5% lower than that of the base metal. Meanwhile, compared with the base metal, the fatigue strength was reduced by 45.5% at 109 cycles of fatigue life. The fracture analysis showed that the fatigue failure of the welded joint of TC17 alloy was caused by the welded pores and the fatigue cracks initiated from the welded pores. A fine granular area (FGA) was observed around the crack initiation region. The existence of pores caused the stress intensity factor of the fine granular area (KFGA) to be inversely proportional to the fatigue life. The KFGA calculation formula was modified and the fatigue crack propagation threshold of the welded joint of TC17 alloy was calculated (3.62 MPa·m1/2). Moreover, the influences of the effective size and the relative depth of the pores on the very long fatigue life of the electron beam welded joint of TC17 titanium alloy were discussed.

Design Flaw Enhanced by Improper Workmanship to Cause Fatigue Failure on Rotor Blade of Compressor Gas Turbine

2014 ◽  
Vol 660 ◽  
pp. 593-597
Author(s):  
Slameto Wiryolukito
Keyword(s):  
Gas Turbine ◽  
Fatigue Failure ◽  
Root Surface ◽  
Rotor Blades ◽  
Blade Surface ◽  
Compressor Blades ◽  
Root Cause ◽  
Root Area ◽  
Failure Event ◽  
Cause Of Failure

Ten stages of Compressor Engine S/N 123 of X-Gas Turbine failed in service prior the schedule for overhaul at 40,000 hour. At the failure event the running hour was 29,600. The maintenance was normally done every 8000 hours including filter and gasket replacement, instrument re-calibration, and bore scope examination. Upon dismantling, it was found one blade at rotor stage #3 failed with facture surface strongly indicated a fatigue failure, defective on stator and rotor blades at downstream, no defective blades at upstream. Detail examination confirm Root Cause of failure on Compressor Blade of X-Gas Turbine were combination of a sharp radius of root chamfer as the major contributor and at lesser extent enhanced by “scratches” exist on root blade free surface. There was no evidences Foreign Objects or corrosion contributed to fail the compressor blades. Blade material was sound and did not contribute to fail the blade. The recommendations to avoid failure reoccurrences were all existing installed rotor blades shall be dismantled and examined for the existence of crack at their root area. Inspection on brand new blades for the existence of scratches on blade surface prior assembly shall be strongly imposed; blade with preexisting scratch shall be rejected. In a design stages, increase the sharp chamfer radius on blade root is worth-while to be analyzed further. Workmanship during blade assembly shall not develop any scratch on blade surface especially on its root surface. A procedure and schedule for inspection on the running blades shall be refined to be able to detect any crack on the operating blades; special attention shall be given on root area.

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