Assessment of compressor blade fatigue life by accelerated method

1981 ◽  
Vol 13 (1) ◽  
pp. 73-75
Author(s):  
P. S. Bekbulatov ◽  
M. E. Kolotnikov ◽  
I. G. Sipukhin
Keyword(s):  
Fatigue Life ◽  
Compressor Blade

Modified Three-Parameter Model to Predict Compressor Blade Fatigue Life under Vibration Loading

2019 ◽  
Vol 32 (4) ◽  
pp. 04019034
Author(s):  
Yakui Zhang ◽  
Shuxiang Guo ◽  
Zhongping Zhang ◽  
Bolin Shang
Keyword(s):  
Fatigue Life ◽  
Compressor Blade ◽  
Vibration Loading

scholarly journals Research on the Fatigue Performance of TC6 Compressor Blade under the CCF Effect

2018 ◽  
Vol 2018 ◽  
pp. 1-10
Author(s):  
Zhang Yakui ◽  
Guo Shuxiang
Keyword(s):  
Fatigue Life ◽  
High Cycle Fatigue ◽  
Low Cycle Fatigue ◽  
Compressor Blade ◽  
Fatigue Performance ◽  
Cycle Fatigue ◽  
Test Rig ◽  
Source Characteristics ◽  
Fracture Appearance ◽  
Fatigue Life Reduction

This paper studied the influence of high and low combined fatigue (CCF) on compressor blade fatigue performance. We investigated the coupling between low cycle fatigue (LCF) loading from centrifugal force with high cycle fatigue (HCF) loading from vibration and determined the blade disc vibration frequency using static analysis at maximum rotational speed. We designed and constructed a combined fatigue test rig, and CCF tests were performed on a TC6 compressor blade to analyze fatigue life characteristics. Results showed that CCF could significantly shorten blade life compared with pure LCF and that larger HCF caused more significant fatigue life reduction. Fatigue source characteristics and CCF fracture appearance were observed and analyzed using a scanning electron microscope (SEM).

scholarly journals Research on Fatigue Damage of Compressor Blade Steel KMN-I Using Nonlinear Ultrasonic Testing

2017 ◽  
Vol 2017 ◽  
pp. 1-11 ◽  
Author(s):  
Pengfei Wang ◽  
Weiqiang Wang ◽  
Jianfeng Li
Keyword(s):  
Fatigue Life ◽  
Fatigue Damage ◽  
Ultrasonic Testing ◽  
Early Stage ◽  
Compressor Blade ◽  
Nonlinearity Parameter ◽  
Nonlinear Ultrasonic ◽  
Blade Steel ◽  
Scanning Electron ◽  
Peak Value

The fatigue damage of compressor blade steel KMN-I was investigated using nonlinear ultrasonic testing and the relation curve between the material nonlinearity parameter β and the fatigue life was obtained. The results showed that the nonlinearity parameter increased first and then decreased with the increase of the fatigue cycles. The microstructures were observed by scanning electron microscopy (SEM). It was found that some small defects like holes and pits appeared in the material matrix with the increase of the fatigue cycles, and the nonlinearity parameter increased correspondingly. The nonlinearity parameter reached the peak value when the microcracks initiated, and the nonlinearity parameter began to decrease when the microcracks further propagated to macrocracks. Therefore, it is proved that the nonlinearity parameter can be used to characterize the initiation of microcracks at the early stage of fatigue, and a method of evaluating the fatigue life of materials by nonlinear ultrasonic testing is proposed.

scholarly journals Numerical Study on Vibration Response and Fatigue Damage of Axial Compressor Blade Considering Aerodynamic Excitation

Metals ◽  
2021 ◽  
Vol 11 (11) ◽  
pp. 1835
Author(s):  
Xi Fu ◽  
Chao Ma ◽  
Jiewei Lin ◽  
Junhong Zhang
Keyword(s):  
Shear Stress ◽  
Fatigue Life ◽  
Fatigue Damage ◽  
Damage Accumulation ◽  
Equivalent Stress ◽  
Axial Compressor ◽  
Compressor Blade ◽  
Torsional Shear ◽  
Fatigue Damage Accumulation ◽  
Fatigue Model

Axial compressor blades with a deformed initial torsion angle caused by aerodynamic excitation resonated at the working speed and changed the rule of fatigue damage accumulation. The fatigue life of a blade has a prediction error, even causing serious flight accidents if the effect of torque causing damage deterioration of the blade fatigue life is neglected. Therefore, in this paper, a uniaxial non-linear fatigue damage model was modified using the equivalent stress with torsional shear stress, and the proposed fatigue model including the torsional moment was used to study the compressor blade fatigue life. Then, the blade numerical simulation model was established to calculate the vibration characteristics under complex loads of airflow excitation and a rotating centrifugal force. Finally, the blade fatigue life under actual working conditions was predicted using the modified fatigue model. The results show that the interaction between centrifugal and aerodynamic loads affects the natural frequency, as the frequencies in modes dominated by bending deformation decreased whereas those dominated by torsional deformation increased. Furthermore, the blade root of the suction surface showed stress concentration, but there is an obvious difference of stress distribution and amplitude between the normal stress and the equivalent stress including torsional shear stress. The additional consideration of the torsional shear stress decreased the predicted fatigue life by 4.5%. The damage accumulation rate changes with the loading cycle, and it accelerates fast for the last 25% of the cycle, when the blade fracture may occur at any time. Thus, the aerodynamic excitation increased the safety factor of blade fatigue life prediction.

scholarly journals Assessment of the Impact of Shot-Peening on the Fatigue Life of a Compressor Blade Subjected to Resonance Vibrations

Materials ◽  
2020 ◽  
Vol 13 (24) ◽  
pp. 5726
Author(s):  
Arkadiusz Bednarz ◽  
Wojciech Z. Misiolek
Keyword(s):  
Fatigue Life ◽  
Shot Peening ◽  
Geometric Model ◽  
Fatigue Analysis ◽  
Compressor Blade ◽  
Strength Analysis ◽  
Equivalent Stresses ◽  
Resonance Vibrations ◽  
Secondary Objective ◽  
The Impact

This publication presents an assessment of the influence of a surface treatment such as shot-peening on the fatigue life of a compressor blade exposed to resonant vibrations. As part of the work, a geometric model of the blade was developed, and a numerical modal and fatigue analysis were performed. The fatigue analysis was based on the Manson–Coffin–Basquin and Ramberg–Osgood models. Additionally, the location of the highest equivalent stresses was established. Based on the results of the strength analysis, two points were identified where a fatigue crack may potentially occur. As part of the work, the influence of different values of residual stresses on the results of the fatigue life was determined. The obtained results were compared to the literature values of fatigue life for this blade. A secondary objective of the study was to determine the size of the grains at various points of the blade, as well as the thickness of the layer plasticized as a result of peening. The relationship between the location of the highest values of the equivalent stresses and the thickness of the plasticized layer was determined. An explanation of the effect of shot-peening on the increase in the fatigue life of the blade was proposed.

scholarly journals Assessment of the Impact of Shot Peening on the Fatigue Life of a Compressor Blade Subjected to Resonance Vibrations

2020 ◽  
Author(s):  
Arkadiusz Bednarz ◽  
Wojciech Misiołek
Keyword(s):  
Fatigue Life ◽  
Shot Peening ◽  
Geometric Model ◽  
Fatigue Analysis ◽  
Compressor Blade ◽  
Resonant Vibrations ◽  
Equivalent Stresses ◽  
Resonance Vibrations ◽  
The Impact ◽  
The Relationship

The publication presents the assessment of the influence of surface treatment such as shot-peening on the fatigue life of a compressor blade exposed to resonant vibrations. As part of the work, a geometric model of the blade was developed and a numerical modal and fatigue analysis were performed. The fatigue analysis was based on the Manson-Coffin-Basquin and Ramberg-Osgood models. As part of the work, the influence of different values of residual stresses on the results of fatigue life was determined. Additionally, the location of the highest equivalent stresses was established. The obtained results of the numerical analyzes were compared with the results presented in the scientific literature. An additional aim of the study was to determine the size of the grains at various points of the blade as well as the thickness of the layer plasticized as a result of peening. The obtained results are presented in the form of tables and charts. The relationship between the location of the highest values of equivalent stresses and the thickness of the plasticized layer was determined. The explanation of the effect of shot peening on the increase in fatigue life of the blade was proposed.

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