An air crash due to failure of compressor rotor

Ejaz, Naveed; Salam, I.; Tauqir, A.

doi:10.1016/j.engfailanal.2006.11.026

Cited by 11 publications

(11 citation statements)

References 2 publications

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“…Fatigue failure on the turbine and compressor of a gas turbine is common. Ejaz, Salam, and Tauqir (2007), examined the crack of a fighter aircraft that resulted from failure of the 9th stage compressor disk of the turbine engine. They concluded that the failure was a result of fatigue crack growth, originating from a hole that had followed machining marks, resulting in a final catastrophic length of 30 mm.…”

Section: Previous Accident Case Studiesmentioning

confidence: 99%

Need for Aerospace Structural Health Monitoring

Wild

Pollock

Abdelwahab

et al. 2021

IJPHM

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Aircraft accidents involving catastrophic fatigue failure have the potential for significant loss of life. The aim of this research was to investigate trends in aircraft fatigue failure accidents to inform aerospace Structural Health Monitoring (SHM) system Research and Development (R&D). The research involved collecting 139 aircraft fatigue failure accident reports from the Aviation Safety Network database, which were coded using a directed content analysis. The trends and features of the categorical data were then explored using an ex-post facto study. The results showed that fatigue failure accidents have increased at a rate of (3.4 ± 0.6)×10-2 per year since the 1920’s. Over the period of the study there were 2098 fatalities in 57 fatal accidents, giving (15.1 ± 1.6) fatalities per accident and a fatal accident percentage of (45 ± 10)%. The data indicates that engine failures combined with smaller aircraft and operators should be the focus of SHM R&D. While there is a desire to further improve safety for large transport category aircraft, results indicate that smaller aircraft and operators have seen a relative increase in fatigue failure accidents, and hence are also in need of SHM systems. Engine and undercarriage systems have the greatest number of fatigue failure accidents associated with them, suggesting these should be the focus of SHM R&D.

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Section: Previous Accident Case Studiesmentioning

confidence: 99%

Need for Aerospace Structural Health Monitoring

Wild

Pollock

Abdelwahab

et al. 2021

IJPHM

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“…The blades of aircraft engine compressors are one of its most important components, ensuring operational safety and aircraft performance [1,3]. The compressor blades run at speeds exceeding 40,000 RPM, generating a pressure increase several dozen times.…”

Section: Introductionmentioning

confidence: 99%

“…When discussing the operating conditions of the aircraft engine's compressor blades, it should also be taken into account that the first stage of the compressor is in particular exposed to collision damage with a hard element sucked into the engine [4]. The occurrence of the resonance situation (caused by vibrations) [6], combined with foreign object damage may be the cause of the crack initiation [1], which may result in engine damage or even failure of the aircraft [3,16].…”

Section: Introductionmentioning

confidence: 99%

Influence of the Cyclic Hardening Model on the Results of the Numerical Analysis of Fatigue Life on Example of the Compressor Blade

Bednarz

2019

Journal of KONES

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The main goal of the presented work is to determine the impact of the cyclic hardening model on the numerical results of the ε-N fatigue test. As an object of study, compressor blade (from PZL-10W helicopter engine) was used. The examined blade was made of EI-961 alloy. In numerical analysis, a geometrical model of the blade with a preliminary defect was created. Geometrical defect – V-notch was created on the leading edge. This defect was introduced in order to weaken the structure of the element and the possibility of observing the crack initiation process (in experimental tests). Material data to ε-N analysis, based on Manson-Coffin-Basquin equation, were estimated for Mitchell’s model. This model was built based on strength data provided by the steel producer. Based on three different models of cyclic hardening (Manson, Fatemi, and Xianxin), a number of load cycles were calculated. Load cycle during numerical analysis was represented as resonance bending with an amplitude of displacement equal to A = 1.8 mm. Obtained results were compared with experimental data. Additionally, the analytical model of ε-N fatigue (depending on the cyclic hardening) was prepared. All the work carried out has been summarized by a comprehensive comparative analysis of the results. Obtained results and dependencies can be used in the selection of an appropriate model of cyclic hardening in further fatigue tests of many aerospace elements.

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“…Scholars at home and aboard have carried out significative research on the impeller failure modes, summing up the following two main reasons for the cause of the impeller failure fracture: one is its own defects or material processing defects and the other is the alternating stress fatigue. The material and manufacturing defects are well understood [2][3][4][5][6][7][8]. It is shown that alternating stress in internal compressor is mainly from unsteady flow and aerodynamic loads [5,[9][10][11][12].…”

Section: Introductionmentioning

confidence: 99%

Study on Impeller Fracture Model Based on Vibration Characteristics and Fractal Theory

Zhang

Yuan

Xie

2015

Advances in Mathematical Physics

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During the operation of centrifugal compressor, failure easily occurs in the presence of complicated external forces. The failure process characterizes with strong nonlinearity, and hence it is difficult to be described by conventional methods. In this paper, firstly, the cracks in different positions are described using crack fractal theory. The basic failure modes of the impeller are summarized. Secondly, a three-dimensional finite element model of the impeller is constructed. Then the von Mises stress under the centrifugal force is calculated, and the corresponding impeller failure process is simulated by “element life and death technology” in ANSYS. Finally, the impeller failure mechanism is analyzed. It can be found that the static stress is not the main cause of the impeller failure, and the dynamic characteristics of the impeller are not perfect because of the pitch vibration modes which appeared in the investigated frequency range. Meanwhile, the natural frequency of the impeller also cannot avoid the frequency of the excitation force.

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An air crash due to failure of compressor rotor

Cited by 11 publications

References 2 publications

Need for Aerospace Structural Health Monitoring

Need for Aerospace Structural Health Monitoring

Influence of the Cyclic Hardening Model on the Results of the Numerical Analysis of Fatigue Life on Example of the Compressor Blade

Study on Impeller Fracture Model Based on Vibration Characteristics and Fractal Theory

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