Crack of a first stage blade in a steam turbine

Nurbanasari, Meilinda; Abdurrachim,

doi:10.1016/j.csefa.2014.04.002

Cited by 30 publications

(10 citation statements)

References 7 publications

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“…Loc1 is a small region of high strain that has been noted in literature as a location for fir-tree blade groove failure (Sz et al (2009)). While Loc2 and Loc3 have been noted as locations for dovetail blade groove failure (Nurbanasari and Abdurrachim (2014)).…”

Section: Temperature and Stress Field Analysismentioning

confidence: 99%

Experimental characterisation and computational modelling of cyclic viscoplastic behaviour of turbine steel

Rae

Benaarbia

Hughes³

et al. 2019

International Journal of Fatigue

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Fully reversed strain controlled low cycle fatigue and creep-fatigue interaction tests have been performed at ±0.7% strain amplitude and at three different temperatures (400°C, 500°C and 600°C) to investigate the cyclic behaviour of a FV566 martensitic turbine steel. From a material point of view, the hysteresis mechanical responses have demonstrated cyclic hardening at the running-in stage and subsequent, hysteresis cyclic softening during the rest of the material life. The relaxation and energy behaviours have shown a rapid decrease at the very beginning of loading followed by quasi-stabilisation throughout the test. A unified, temperature-and rate-dependent visco-plastic model was then developed and implemented into the Abaqus finite element (FE) code through a user defined subroutine (UMAT). The material parameters in the model were determined via an optimisation procedure based on a genetic solver. The multi-axial form of the constitutive model developed was demonstrated by analysing the thermomechanical responses of an industrial gas turbine rotor subjected to in-service conditions. A sub-modelling technique was used to optimise the FEA. A 2D global model of the rotor with a 3D sub-model of the second stage of the low pressure turbine were then analysed in turn. The complex transient stress and accumulated plastic strain fields were investigated under realistic thermo-mechanical fatigue loading (start-up and shutdown power plant loads). The sub-model was then used for local analysis leading to identification of potential crack initiation sites for the presented types of blade roots.

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Section: Temperature and Stress Field Analysismentioning

confidence: 99%

Experimental characterisation and computational modelling of cyclic viscoplastic behaviour of turbine steel

Rae

Benaarbia

Hughes³

et al. 2019

International Journal of Fatigue

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“…In this case, two initial cracks were initiated by the pitting corrosion in the outer surface of crown area and that pitting corrosion triggered the initial crack of the fatigue fracture. In fact, it was not surprising as the ash handling unit was in the aggressive environment where Clions catalized the pitting corrosion [12][13][14][15]. 8 showed the load and raction load during the shackle chain was operated.…”

Section: Failure Investigationmentioning

confidence: 99%

Metallurgical Analysis of Fatigue Failure in Submerge Chain Conveyor

Sihotang¹,

Nurbanasari²,

Abdurrachim³

et al. 2020

International Journal of Engineering Research and Technology

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Ash handling unit is one of the crucial part of the operation of a coal fired power plant (CFPP). This paper focused on the investigation of shackle chain failure in ash handling unit of a 600 MW CFPP. The failure caused disruption to the operating system of the CFPP. To improve the chain system in order to prevent similar failure in the near future, the metallurgical failure analysis was conducted on failed shackle chain through crack observation using optical and electron microscope and Vickers hardness test. Crack surface observation of failed shackle chain using Scanning Electron Microscope (SEM) revealed that the failure of shackle chain was primarily due to the fatigue failure which was proven by the presence of beachmarks. In addition, there were two initial cracks which were caused by pitting corrosion. The clearance (gap) occurred in the bolt connection system caused the fatigue load which in turn resulted in failure to the CFPP operation. This research suggested preventive measures to be taken to avoid similar problem in the future.

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“…Therefore, considerable effort is being made to investigate the causes of the disturbances of their extensively stressed parts, such as the rotor disks and blades. The rotor blades, which are most heat-stressed, are often a subject of the breakage in their disk fastening points, either due to fatigue or corrosion cracking (Nurbanasari and Abdurrachim, 2014;Bhagi et al, 2013). In aviation engine manufacture, it is necessary to determine operating cycles of the future engine.…”

Section: Introductionmentioning

confidence: 99%

Fatigue stress analysis of the DV-2 engine turbine disk

Čerňan

Semrád

Draganová

et al. 2019

AEAT

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Purpose The purpose of this study is to improve life prediction of certain components. Fatigue of the high-stressed structural elements is an essential parameter that affects the lifetime of such components. In particular, aviation engines are devices whose failure due to fatigue failure of one of the important components can lead to fatal consequences. Design/methodology/approach In this study, two analyses in the turbine disk of the jet engine during the simulated operating load were performed: The first one was the analysis of the heat-induced stresses using the finite element method. The goal of the second analysis was to determine the residual fatigue strength of a loaded disk by the software tool using the Palmgren - Miner Linear Damage Theory. Findings The results showed a high degree of similarity with the real tests performed on the aircraft engine and revealed the weak points in the design of the jet engine. Research limitations/implications It should be mentioned that without appropriate experiments, results of this analysis could not be verified. Practical implications These results are helpful in the re-designing of the jet engines to increase their technical feasibility. Originality/value Such analysis has been realized in the DV-2 jet engine research and development program for the first time in the history of jet engine manufacturing process in Slovakia and countries of Eastern Europe region.

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Crack of a first stage blade in a steam turbine

Cited by 30 publications

References 7 publications

Experimental characterisation and computational modelling of cyclic viscoplastic behaviour of turbine steel

Experimental characterisation and computational modelling of cyclic viscoplastic behaviour of turbine steel

Metallurgical Analysis of Fatigue Failure in Submerge Chain Conveyor

Fatigue stress analysis of the DV-2 engine turbine disk

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