Implications of engine deterioration for a high-pressure turbine-blade's low-cycle fatigue (LCF) life-consumption

Naeem, Muhammad; Singh, Riti; Probert, Douglas

doi:10.1016/s0142-1123(99)00025-0

Cited by 35 publications

(16 citation statements)

References 14 publications

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“…[1][2][3][4] Some investigators have shown that the coating decreases the fatigue life. Others report no detrimental coating effects or even fatigue life impotents.…”

Section: Introductionmentioning

confidence: 99%

“…A number of studies have been performed on the mechanical properties of Rene´80 (provided by Nategh, Shaif University, Tehran, Iran). [4,[17][18][19][20][21][22] There are few references in the field of influence of aluminide diffusion coating on the mechanical properties of this alloy. [1,3,6,13] Antolovich et al [19] attributed the cyclic deformation mechanism of Rene¢ 80 at 871°C, 982°C, R = 0.05, and strain rates of 0.5, 50 pct/min to the loss of coherency due to c¢ particle coarsening in which micrographs of misfit dislocation were presented as evidence.…”

Section: Introductionmentioning

confidence: 99%

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Mechanical Properties of Uncoated and Aluminide-Coated René 80

Rahmani¹,

Nategh

2009

Metall Mater Trans A

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Nickel-base superalloys such as Rene´80 are widely used in manufacturing aircraft turbine blades. They are usually coated in order to increase their wear, oxidation, erosion, and hot corrosion properties against environmental degradation. In this article, the mechanical behavior (tensile and low-cycle fatigue (LCF)) of uncoated and aluminide-coated (CODEP-B) Rene8 0 has been studied at 871°C and 982°C. Experimental results show that the tensile properties of coated specimens are relatively lower than those of uncoated ones in the same conditions, but application of coating increases the LCF life of Rene´80 at T = 871°C, 982°C, R = (e min /e max ) = 0, strain rate of 2 9 10 À3 s À1 , and De t = 0.8 pct. Scanning electron microscopy (SEM) studies of coated specimens at N = Nf show that the nucleation of cracks occurs merely in substrate, but cracks start from the surfaces in uncoated specimens. Transmission electron microscopy (TEM) investigations have been performed on fractured uncoated specimens to evaluate the microstructures at different temperatures. The misfit dislocation, pair dislocations, and cutting of c¢ were observed at T = 871°C and 982°C. The TEM studies also showed that at 982°C stacking fault was observed in c¢ particles.

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“…[1][2][3][4] Some investigators have shown that the coating decreases the fatigue life. Others report no detrimental coating effects or even fatigue life impotents.…”

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Mechanical Properties of Uncoated and Aluminide-Coated René 80

Rahmani¹,

Nategh

2009

Metall Mater Trans A

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“…The first is the setting of an accurate life expectancy. The second process is a means for determining and controlling the rate of life usage in actual service . For turbine blades, there are usually LCF problems and creep deformations during every flight mission cycle.…”

Section: Introductionmentioning

confidence: 99%

Accelerated LCF‐creep experimental methodology for durability life evaluation of turbine blade

Shi

Yang

et al. 2018

Fatigue Fract Eng Mat Struct

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This paper proposes an accelerated low cycle fatigue (LCF)‐creep experimental methodology in laboratory to investigate the durability life of turbine blades. A typical mission profile of the turbine blade was obtained by means of rain flow counting method, considering both the actual flight condition and ground test data. Finite element analysis (FEA) was conducted to obtain the stress and temperature fields of turbine blade. A test system was constructed to conduct LCF‐creep experiments of turbine blades, simulating the stress and temperature distributions of critical section properly. LCF‐creep experiments of full‐scale turbine blades were performed under a trapezoidal loading spectrum. Experiment results showed that the durability life of turbine blade based on numerical method was longer than that based on this experimental methodology, even an order of magnitude. Furthermore, this experimental methodology helped to extend the service life of this blade safely, and its validity was verified in actual service condition.

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“…Gelmedin and Lang [17] studied IN 713C fatigue behaviors under LCF, HCF, and CCF conditions and found that, compared with the pure LCF loading, the superimposed HCF could dramatically shorten blade lifetime if its amplitude was high enough. Many studies have considered the same problems of the combined fatigue effects, researching that combined fatigue life is more important and complex, and most studies considered turbine blades with few considering compressor blades [18][19][20][21][22].…”

Section: Introductionmentioning

confidence: 99%

Research on the Fatigue Performance of TC6 Compressor Blade under the CCF Effect

Zhang

Guo

2018

International Journal of Aerospace Engineering

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This paper studied the influence of high and low combined fatigue (CCF) on compressor blade fatigue performance. We investigated the coupling between low cycle fatigue (LCF) loading from centrifugal force with high cycle fatigue (HCF) loading from vibration and determined the blade disc vibration frequency using static analysis at maximum rotational speed. We designed and constructed a combined fatigue test rig, and CCF tests were performed on a TC6 compressor blade to analyze fatigue life characteristics. Results showed that CCF could significantly shorten blade life compared with pure LCF and that larger HCF caused more significant fatigue life reduction. Fatigue source characteristics and CCF fracture appearance were observed and analyzed using a scanning electron microscope (SEM).

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Implications of engine deterioration for a high-pressure turbine-blade's low-cycle fatigue (LCF) life-consumption

Cited by 35 publications

References 14 publications

Mechanical Properties of Uncoated and Aluminide-Coated René 80

Mechanical Properties of Uncoated and Aluminide-Coated René 80

Accelerated LCF‐creep experimental methodology for durability life evaluation of turbine blade

Research on the Fatigue Performance of TC6 Compressor Blade under the CCF Effect

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