Fractographic investigations of the failure of L-1 low pressure steam turbine blade

Bhagi, Loveleen Kumar; Gupta, Prosenjit; Rastogi, Vipul

doi:10.1016/j.csefa.2013.04.007

Cited by 37 publications

(14 citation statements)

References 3 publications

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“…While turbine blades are subjected to a very strenuous environment inside a gas turbine, such as high temperatures, stresses, and vibration, leading to blade failures, potentially destroying the engine, even though turbine blades are carefully designed to resist these conditions. The first stage of a gas turbine faces temperatures around 1370 °C, that can weaken the blades and make them more susceptible to creep and corrosion failures [4]. High stress from centrifugal force and fluid forces that can cause fracture, yielding, or creep failures of blades while vibrations can entail fatigue failures.…”

Section: Introductionmentioning

confidence: 99%

Scheduling Remanufacturing Activities for the Repair of Turbine Blades: An Approximate Branch and Bound Approach to Minimize a Risk Measure

Liu

Urgo

2021

Lecture Notes in Mechanical Engineering

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Refurbished products are gaining importance in many industrial sectors, specifically high-value products whose residual value is relevant and guarantee the economic viability of the remanufacturing at an industrial level, e.g., turbine blades for power generation. In this paper we address the scheduling of re-manufacturing activities for turbine blades. Parts entering the process may have very different wear state or presence of defects. Thus, the repair process is affected by a significant degree of uncertainty. To cope with this, the proposed approach pursues robust schedules minimizing the risk associated to a timely completion time. An approximate branch and bound algorithm is developed grounding on the estimation of the lower bound of the makespan. The viability and efficiency of the approach is assessed through computational experiments grounding on the industrial case under study and a comparison is operated among alternative scheduling approaches.

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Section: Introductionmentioning

confidence: 99%

Scheduling Remanufacturing Activities for the Repair of Turbine Blades: An Approximate Branch and Bound Approach to Minimize a Risk Measure

Liu

Urgo

2021

Lecture Notes in Mechanical Engineering

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“…Degradation and failure of gas-turbine blades can obviously have severe negative implications for the integrity and functionality of gas turbines and hence the output of a power plant. Failures of gas-turbine blades can be due to creep damage, high-temperature corrosion, high-temperature oxidation, fatigue, erosion, and foreign object damage [1][2][3][4][5][6][7][8][9][10][11][12][13][14][15]. Obviously, in most cases the failure is due to the interrelation of more than one failure mechanism [2].…”

Section: Introductionmentioning

confidence: 99%

Corrosion-Fatigue Failure of Gas-Turbine Blades in an Oil and Gas Production Plant

et al. 2020

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This paper investigates the root cause of a failure in gas-turbine blades, made of Nimonic-105 nickel-based superalloy. The failure was reported in two blades in the second stage of a turbine-compressor of a gas turbine in the hot section. Two failed blades were broken from the root and from the airfoil. The failure took place after 20 k h of service exposure in the temperature range 700–850 °C, with the rotating speed being in the range 15,000–16,000 rpm. The microstructures of the failed blades were studied using optical/electron microscopes. Energy dispersive X-ray spectroscopy (EDS) was employed for phase identification. Results showed that failure first initiated from the root. The dominant failure mechanism in the root was concluded to be corrosion-fatigue. The failure scenario was suggested based on the results obtained.

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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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Fractographic investigations of the failure of L-1 low pressure steam turbine blade

Cited by 37 publications

References 3 publications

Scheduling Remanufacturing Activities for the Repair of Turbine Blades: An Approximate Branch and Bound Approach to Minimize a Risk Measure

Scheduling Remanufacturing Activities for the Repair of Turbine Blades: An Approximate Branch and Bound Approach to Minimize a Risk Measure

Corrosion-Fatigue Failure of Gas-Turbine Blades in an Oil and Gas Production Plant

Fatigue stress analysis of the DV-2 engine turbine disk

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