Mechanism and modeling of fatigue crack initiation and propagation in the directionally solidified CM186 LC blade of a gas turbine engine

Salehnasab, B.; Poursaeidi, Esmaeil

doi:10.1016/j.engfracmech.2019.106842

Cited by 26 publications

(7 citation statements)

References 30 publications

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“…Journal of Physics: Conference Series 2691 (2024) 012011 IOP Publishing doi:10.1088/1742-6596/2691/1/012011 2 Salehnasab [3] proposed the mechanism and model of fatigue crack initiation and propagation in blade CM186LC directionally solidified material and calculated the crack propagation direction based on the maximum energy release rate criterion. Wang [4] proposed a high and low circumferential composite fatigue life prediction model based on the improved-Zhu model.…”

Section: Matma-2023mentioning

confidence: 99%

Failure analysis of large and complex engine blades based on experimental research

Chen,

Feng,

Ding

2024

J. Phys.: Conf. Ser.

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On a certain day in December 2022, a GE90 engine equipped by an airline experienced a surge during flight. Ground inspection revealed broken blades of the 9-stage high-pressure compressor. To identify the cause of its fracture failure, the macroscopic fracture surface was first analyzed. Obvious fatigue crack propagation characteristics were found at the blade cross-section. Small pits formed by the impact were observed at the crack source location, indicating that the blade was first formed into a circular arc-shaped impact wound after being impacted by an external object. In the subsequent service process, under continuous vibration, fatigue cracks are formed at the impact point as the crack source and gradually propagate, ultimately leading to blade fracture and failure. To further explore the source of foreign objects causing impact damage, the surface scanning method using energy spectrum analysis was used. An enriched region of C element was found near the impact point. However, due to the lack of conditions for the formation of C combustion products at the compressor location, it can be considered that the foreign object may have come from external sources.

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Section: Matma-2023mentioning

confidence: 99%

Failure analysis of large and complex engine blades based on experimental research

Chen,

Feng,

Ding

2024

J. Phys.: Conf. Ser.

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“…Experimental Test. In 2020, Salehnasab and Poursaeidi [28] pointed out that the high centrifugal stress and thermal loads in start-up and shutdown are responsible for the low cycle life of blades. Thus, in the current work, the fatigue ver-ification test at room temperature is conducted.…”

Section: 22mentioning

confidence: 99%

Research on the Fatigue of Small Impulse Turbine Blade Based on the Numerical Simulation and Experimental Tests

Liu¹,

Liang

Liu

et al. 2021

International Journal of Aerospace Engineering

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Reusable spacecraft is increasingly attracting researchers’ attention. However, the experimental investigations on the turbine blade of the rocket engine are rarely published. Thus, the fatigue of a small impulse rocket turbine blade is explored in the current work. First, the specimen and the electrode of electrical discharge machining are carefully designed. Then, the electrical discharge machining is used to machine the specimen. To study the fatigue properties, the finite element analyses are separately performed on the blade model and the specimen. Based on the numerical results, a fatigue test is carried out to reproduce the most vulnerable position. Finally, the microstructural structures of the specimen are detected using the scanning electron microscope (SEM). Results show that (1) different from the aviation field, the specimen is unable to be machined with the welding method because it destroys the crucial details and the mechanical properties; (2) the maximum plastic strain is present at the leading edge close to the hub, at which a 760 μm corner crack appears at the 10113th fatigue cycle. This work provides a feasible method of using the EDM process to machine specimen for the small impulse turbine blade.

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Section: Introductionmentioning

confidence: 99%

“…Therefore, the failure of the blade can be result from low cycle fatigue [2][3] , creep-fatigue, thermal fatigue [9] and thermal mechanical fatigue [10] . According to the temperature and stress/strain history at the detailed location of the blade [4][5] , low cycle fatigue may be the main failure mode under the platform. Therefore, one purpose in the literatures to optimize the turbine blade structure was stress minimization [1] .The complexity of turbine blade structure brings great difficulties to parametric optimization.…”

mentioning

confidence: 99%

“…Due to the high radius of the structure and the large mass of the blade, the gas turbine blades are subjected to huge mechanical loads, high temperature loads, aerodynamic loads, etc., and it is difficult to design the structural strength and life. Domestic scholars [2][3][4][5][6][7][8][9][10] have carried out certain research work on gas turbine blade structure design and life analyzer technology.Gas turbine blades in aero-engines experience complex loadings, depending on the location of the structure, design method and service. Therefore, the failure of the blade can be result from low cycle fatigue [2][3] , creep-fatigue, thermal fatigue [9] and thermal mechanical fatigue [10] .…”

mentioning

confidence: 99%

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Structure Design and Optimization of a gas turbine blade

Qian¹,

Li²

2022

J. Phys.: Conf. Ser.

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Mechanism and modeling of fatigue crack initiation and propagation in the directionally solidified CM186 LC blade of a gas turbine engine

Cited by 26 publications

References 30 publications

Failure analysis of large and complex engine blades based on experimental research

Failure analysis of large and complex engine blades based on experimental research

Research on the Fatigue of Small Impulse Turbine Blade Based on the Numerical Simulation and Experimental Tests

Structure Design and Optimization of a gas turbine blade

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