Relationship Between γ′ Phase Degradation and In-Service GTD-111 First-Stage Blade Local Temperature

Villada, J. A.; Bayro-Lazcano, R. G.; Martínez‐Franco, Enrique; Espinosa-Arbeláez, D.G.; González‐Hernández, J.; Alvarado-Orozco, J.M.

doi:10.1007/s11665-019-03994-4

Cited by 8 publications

(4 citation statements)

References 22 publications

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“…It is well known that GTD-111 undergoes a microstructural degradation caused mainly by γ'-phase coarsening and coalescence. Several authors have found a gradual increase in γ' particle size, depending on the temperature and thermal exposure time [15,33,34]. Therefore, the size of γ' particles can be used to evaluate the in-service temperature at different blade locations.…”

Section: First-stage Turbine Bladementioning

confidence: 99%

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Computational and Experimental Study on Failure Mechanism of a GTD-111 First-Stage Blade of an Industrial Gas Turbine

Bayro-Lazcano,

Piedra-Gonzalez,

García-Moreno

et al. 2023

Metals

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This paper investigates the root cause of a recurring failure observed in the first-stage blades of an industrial gas turbine. The failure involves the loss of the trailing edge tip of the blades. The study employs a combination of metallographic analysis and computational simulations utilizing the finite element method and computational fluid dynamics. The metallographic analysis reveals significant degradation in the GTD-111 nickel-based superalloy within the region where the failure occurs. This degradation is characterized by the coarsening and coalescence of the gamma prime phase, which can be attributed to localized overheating. Additionally, the computational study enables the calculation of the trajectory, pressure, and temperature profiles of the hot gases, as well as the distribution of temperatures within the blade. These findings demonstrate that the cooling airflow is influenced by the hot gas flow, particularly in the vicinity of the fault location, owing to the orientation of the cooling ducts, which results in overheating in this area. Ultimately, the temperatures derived from the microstructural analysis using the Ostwald-ripening theory align remarkably well with the results obtained from the simulation, validating the accuracy of the computational model. By combining metallographic analysis and computational simulations, this study provides crucial insights into the failure mechanism of the first-stage blades.

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Section: First-stage Turbine Bladementioning

confidence: 99%

“…Another alternative approach to evaluating the in-service temperature is assessing the γ'-phase (Ni 3 Ti) evolution [11][12][13][14][15]. It is well known that nickel-based superalloys undergo microstructural degradation during their lifetime caused by γ'-phase coarsening and coalescence [14].…”

Section: Introductionmentioning

confidence: 99%

Computational and Experimental Study on Failure Mechanism of a GTD-111 First-Stage Blade of an Industrial Gas Turbine

Bayro-Lazcano,

Piedra-Gonzalez,

García-Moreno

et al. 2023

Metals

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“…Nickel-based superalloys have ideal properties in critical working conditions due to their multiphase and complex microstructure, which includes γ phase, γ-γ eutectic, Cr-Mo-rich borides, Ni-Zr intermetallics, and Cr-Ti-Ta-rich carbides [3]. Among these materials, GTD-111 superalloy is used as the first-row blades of gas turbines due to its ideal chemical composition [4]. However, using this material without a coating is strictly not recommended.…”

Section: Introductionmentioning

confidence: 99%

The Effect of an Ultrasonic Field on the Microstructure and Tribological Behavior of ZrB2/ZrC+Ni60A/WC Composite Coating Applied by Laser Cladding

Wei,

Najafi,

Taheri

et al. 2023

Coatings

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Ni60A/WC composite coating reinforced with ZrB2/ZrC was layered on GTD-111 superalloy by laser cladding. The effect of an ultrasonic field on coating formation, microstructure, microhardness, and wear was investigated and analyzed. The results showed that the resulting coating had pores and microcracks, which were removed when using an ultrasonic field. Ultrasonic fields increased the heat input and increased the dimensions of the coating pool by creating a cavitation effect. The dendrites of the coating microstructure were mainly composed of Zr(B, C) and ZrC blocks and small α-Zr dendrites. The mechanical vibrations resulting from the application of ultrasonic fields caused the crushing of the growing dendrites, and as a result, the grains and dendrites crumbled. By decreasing the grain size, the average hardness increases from 312 HV for coating without an ultrasonic field to 617 HV for coating with 300 W ultrasonic power. The results of the wear test also showed that the sample coated with 300 W of ultrasonic power, with a coefficient of friction of 0.41 and scar wear of 6.8 µm, has the highest wear resistance due to the removal of porosity and the presence of equiaxed grains on the top and bottom of the clad zone.

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“…It also contributes to the formation of some degraded zones with locally deteriorated thermal and mechanical properties. This kind of damage may cause, for example, the overheating and fatigue cracking of the blade's superalloy [31][32][33]. Excessively high temperatures exceeding nominal temperatures which persist for a long time as well as the occurrence of high centrifugal forces during rotation can result in superalloy creep [18,34,35].…”

Section: Introductionmentioning

confidence: 99%

Investigation of the Relationship between Degradation of the Coating of Gas Turbine Blades and Its Surface Color

et al. 2021

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This article presents issues concerning the relationship between the degradation of the coating of gas turbine blades and changes in the color of its surface. Conclusions were preceded by the determination of parameters characterizing changes in the technical condition of protective coatings made based on a metallographic examination that defined the morphological modifications of the microstructure of the coating, chemical composition of oxides, and roughness parameters. It has been shown that an increased operating time causes parameters that characterize the condition of the blades to deteriorate significantly. Results of material tests were compared with those of blade surface color analyses performed using a videoscope. Image data were represented in two color models, i.e., RGB and L*a*b* with significant differences being observed between parameters in both representations. The study results demonstrated a relationship between the coating degradation degree and changes in the color of the blade’s surface. Among others, this approach may be used as a tool to assess the condition of turbine blades as well as entire gas turbines.

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Relationship Between γ′ Phase Degradation and In-Service GTD-111 First-Stage Blade Local Temperature

Cited by 8 publications

References 22 publications

Computational and Experimental Study on Failure Mechanism of a GTD-111 First-Stage Blade of an Industrial Gas Turbine

Computational and Experimental Study on Failure Mechanism of a GTD-111 First-Stage Blade of an Industrial Gas Turbine

The Effect of an Ultrasonic Field on the Microstructure and Tribological Behavior of ZrB2/ZrC+Ni60A/WC Composite Coating Applied by Laser Cladding

Investigation of the Relationship between Degradation of the Coating of Gas Turbine Blades and Its Surface Color

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