Creep Life Degradation and Microstructure Degeneration in a Low-Pressure Turbine Blade of a Military Aircraft Engine

Sahoo, Bijaylaxmi; Panigrahi, S. K.; Satpathy, R. K.

doi:10.1007/s11668-017-0271-x

Cited by 6 publications

(3 citation statements)

References 17 publications

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“…The findings indicate that the model exhibited a high degree of accuracy in forecasting the lifespan. The creep life of blades was assessed by Sahoo et al [37] using stress fracture testing, while the damage to the coating was evaluated through coating expansion and secondary reaction zone (SRZ). This study investigates the impact of aluminum coating on the surface of a deformable alloy blade composed of nickel on both the creep life of the blade and the microstructure degradation of the blade during its service.…”

Section: Review On Creep Of Aircraft Componentsmentioning

confidence: 99%

Review on Creep Phenomenon and Its Model in Aircraft Engines

Yuan,

Chenglong,

Yongchao

et al. 2023

International Journal of Aerospace Engineering

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The aircraft is subjected to high-temperature and high-pressure conditions during flight, which renders it susceptible to the occurrence of creep phenomenon. Several academics have conducted extensive research on this issue. This research paper provides a comprehensive overview of the existing literature on creep phenomena in aircraft engines. First, several classical creep calculation models are enumerated and categorized as creep life calculation, creep-fatigue life calculation, and creep deformation calculation. Studies on creep phenomena are conducted in various components of aircraft engines, such as the engine’s turbine blades, turbine disks, and combustion chambers. The creep behavior of turbine blades in aircraft engines has been extensively researched. Furthermore, the protective measures aimed at mitigating creep are presented. Materials with high creep resistance can be used, and alternative fuels could be implemented. This paper provides an in-depth analysis of the advantages of creep in aircraft, presented in a favorable perspective. Finally, the prospective future research direction is discussed.

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Section: Review On Creep Of Aircraft Componentsmentioning

confidence: 99%

Review on Creep Phenomenon and Its Model in Aircraft Engines

Yuan,

Chenglong,

Yongchao

et al. 2023

International Journal of Aerospace Engineering

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“…Precision products made of heat-resistant nickel alloys, such as Inconel 718 and Nicrofer 5219 Nb, are more than 50% of the mass of modern aircraft gas turbine engines due to the unique physical and mechanical properties of these materials and their ability to function under conditions of increased contact stresses, high operating temperatures, and corrosive and erosive effects of vapors and gases [1][2][3][4][5]. The scientific group of Kumar, A., in their study of the formation of fatigue cracks in gas turbine engines [1], studied the liquid corrosion of a nickel alloy with lead, which was a critical factor in the actual destruction of gas turbine engines with a relatively short product life cycle, according to their study and the official conclusion of the investigation.…”

Section: Introductionmentioning

confidence: 99%

“…The research group of Sahoo, B. [3] discussed the bulk properties of a military aircraft's gas turbine engine parts that determine the product life and are decided by the aero-thermal degradation and microstructure degeneration of nickel alloy despite aluminide coating. The coarsening of gamma prime and the degeneration of carbides in the bulk material microstructure were evaluated.…”

Section: Introductionmentioning

confidence: 99%

The Effectiveness of Diamond-like Carbon a-C:H:Si Coatings in Increasing the Cutting Capability of Radius End Mills When Machining Heat-Resistant Nickel Alloys

et al. 2022

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The main purpose of this paper was to study the efficiency of using diamond-like carbon (DLC) coatings based on a-C:H:Si with a pre-formed CrAlSiN sublayer to increase the cutting ability of ball end mills made of KFM-39 cemented carbide at a speed of 150–250 m/min in milling aircraft-grade Inconel 718, and to assess the DLC coating effect on the quality of the machined surface. DLC coating performance was quantified against uncoated carbide ball end mills and the proven TiN–AlN–TiAlN gradient multilayer coating at elevated temperatures measured by the natural thermocouple method. The temperature near the cutting edge is the factor determining the wear intensity in the tool contact surfaces in milling hard-to-machine nickel alloys to the greatest extent. Thermo-EMF (electromotive force) was recorded and converted into temperatures by calibration charts. The behavior of CrAlSiN–DLC and TiN–AlN–TiAlN coatings was compared with the results of high-temperature tribological tests on a ball-on-disc friction machine. For the CrAlSiN–DLC coating at cutting speeds of 150 and 200 m/min (<650 °C), the milling time until critical flank face wear (0.4 mm) was more than 67 and 50 min, respectively (1.4–1.5 times longer than an uncoated tool and about 1.3 times longer than the TiN–AlN–TiAlN coating). The CrAlSiN–DLC coating was characterized by a minimum adhesion amount.

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Creep Failure in Aeroengine Components

Sanchez,

Qiu

2024

Sustainable Aviation

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Creep Life Degradation and Microstructure Degeneration in a Low-Pressure Turbine Blade of a Military Aircraft Engine

Cited by 6 publications

References 17 publications

Review on Creep Phenomenon and Its Model in Aircraft Engines

Review on Creep Phenomenon and Its Model in Aircraft Engines

The Effectiveness of Diamond-like Carbon a-C:H:Si Coatings in Increasing the Cutting Capability of Radius End Mills When Machining Heat-Resistant Nickel Alloys

Creep Failure in Aeroengine Components

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