Failure analysis of generator rotor fan blades

Poursaeidi, Esmaeil; Salavatian, M.

doi:10.1016/j.engfailanal.2006.11.042

Cited by 24 publications

(11 citation statements)

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“…Case study (a) In [5] the authors investigated the fracture of a generator turbine blade which occurred shortly after the last overhaul. Based on their fracture mechanics analysis they concluded that the problem consisted in aerodynamical disturbances but they did not mention whether this kind of loading has already been considered at the design stage or not.…”

Section: Questionmentioning

confidence: 99%

“…Note, however, that the crack had spread across more than half the circumference of the tube at failure (2 = 195 o ). The coupler was hardly M A N U S C R I P T ACCEPTED MANUSCRIPT 5 designed for a crack of such dimension. Therefore, as in case study (a), the problem is rather one of non-existent or insufficient quality control or regular ins-service inspection.…”

Section: Questionmentioning

confidence: 99%

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Fracture mechanics as a tool in failure analysis — Prospects and limitations

Zerbst

Klinger

Clegg

2015

Engineering Failure Analysis

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Section: Questionmentioning

confidence: 99%

Section: Questionmentioning

confidence: 99%

Fracture mechanics as a tool in failure analysis — Prospects and limitations

Zerbst

Klinger

Clegg

2015

Engineering Failure Analysis

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“…Occasionally, damage also occurs at the trailing edge of the blade. The work of the blade (containing a notch formed as a result of a collision with a hard object) under resonance conditions may cause rapid initiation of cracks and fatigue damage, resulting in damage and immobilization of the engine [4,5].…”

Section: Introductionmentioning

confidence: 99%

“…The problem of operational damage of the compressor blades has been the subject of research by many authors [2][3][4][5]. In these studies, the attention was focused mainly on explaining the causes of cracks.…”

Section: Introductionmentioning

confidence: 99%

Numerical and Experimental Assessment of the Effect of Residual Stresses on the Fatigue Strength of an Aircraft Blade

Bednarz

Misiołek

2021

Materials

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The work presents the results of numerical fatigue analysis of a turbine engine compressor blade, taking into account the values of initial stresses resulting from surface treatment-shot-peening. The values of the residual stresses were estimated experimentally using X-ray diffraction. The paper specifies the values of the residual stresses on both sides of the blade and their reduction due to cutting through the blade-relaxation. The obtained values of the residual stresses were used as initial stresses in the numerical fatigue analysis of the damaged compressor blade, which was subjected to resonant vibrations of known amplitude. Numerical fatigue ε-N life analysis was based on several fatigue material models: Manson’s, Mitchell’s, Baumel-Seeger’s, Muralidharan-Manson’s, Ong’s, Roessle-Fatemi’s, and Median’s, and also on the three models of cyclic hardening: Manson’s, Xianxin’s, and Fatemi’s. Because of this approach, it was possible to determine the relationship between the selection of the fatigue material ε-N model and the cyclic hardening model on the results of the numerical fatigue analysis. Additionally, the calculated results were compared with the results of experimental research, which allowed for a substantive evaluation of the obtained results. These results are of great scientific and practical importance. The problem of determining the fatigue life of blades with defects operating under resonance vibrations is one of the original tasks in the field of fracture mechanics and experimental mechanics. The results obtained are of great importance in the aviation industry and can be used during engine maintenance and inspections to assess the suitability of blades with defects in terms of the needs of further work. This aspect of engineering maintenance is of great importance from the aircraft safety point of view.

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“…During aero-engine working, the compressor blades easily occur fatigue failure under complex loads, which is the main failure form for the blade [1][2][3][4]. Once the blade failure, a catastrophic accident will be caused in the engine and even the aircraft [5,6].…”

Section: Introductionmentioning

confidence: 99%

Study on Blade Fatigue Life of Rotating Power Machinery

Kou

Zhang

2016

MATEC Web Conf.

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Abstract. The linear damage model (LDM) is widely applied in engineering calculation, but it does not consider the relationship between damage variable and load parameters. Therefore, the life prediction based on LDM is not satisfied for the aero-engine blades. Besides, it easily brings about error in predicting fatigue life by common nonlinear damage model which neglect the influence of torsional stress. Hence, a modified nonlinear continuum damage model (CDM) is put forward based on Chaboche nonlinear damage model in this research. And to determine the damage and fatigue life of TC4 material used in aero-engine blades, axial tension and compression fatigue test is conducted. Compared with LDM results, the fatigue life prediction results of the modified CDM in this work show a good agreement with the tests data. So the correctness of the modified model is verified. Finally, the fatigue life of a certain aero-engine high pressure compressor blade is predicted by the modified nonlinear continuum damage model.

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Failure analysis of generator rotor fan blades

Cited by 24 publications

References 0 publications

Fracture mechanics as a tool in failure analysis — Prospects and limitations

Fracture mechanics as a tool in failure analysis — Prospects and limitations

Numerical and Experimental Assessment of the Effect of Residual Stresses on the Fatigue Strength of an Aircraft Blade

Study on Blade Fatigue Life of Rotating Power Machinery

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