Influence of microstructure degradation induced by pretreatment on the creep behavior in Ni-based single-crystal superalloy with different orientations

Gan, Wenyan; Gao, Hangshan; Zhao, Ye; Zhou, Wen; Lu, Guangxian; Jiang, Bo; Yue, Zhufeng

doi:10.1557/jmr.2020.35

Cited by 7 publications

(3 citation statements)

References 40 publications

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“…Recent decades have seen an increasing interest in estimating the remaining creep lifetimes of turbine blades as a means of ensuring the safety of engines. Gan et al (2020) introduced the initial damage terms that are related with the topologically close-packed (TCP) phase and the coarsen γ′ precipitates when predicting the remaining lifetime. Tian et al (2011) considered the micropores in the lifetime prediction model.…”

Section: Introductionmentioning

confidence: 99%

Dependence of microstructural evolution on the geometric structure for serviced DZ125 turbine blades

Xie

Zhao

et al. 2023

Front. Mater.

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The turbine blades were directionally solidified by a high-rate solidification process by the Bridgman technique using directional solidified Ni-based master superalloy DZ125 and operated on the engine bench with a high-temperature gas environment of more than 1500 °C from combustor and high-speed rotation of more than 13500 rpm for 400 h. A service-environment-based model was put forward to simulate the distribution of temperature and stress on the DZ125 blade in service. It was found that the distribution of temperature and stress on the serviced DZ125 blade was closely related to its geometric structure. The microstructural evolution of the serviced DZ125 blade was analyzed and the variations of microstructures with temperature and stress were investigated by using a scanning electron microscope. The results revealed that the evolution process of microstructures on the serviced DZ125 blade was different from that of the standard sample tested at constant temperature and uniaxial tensile stress. The reason for this discrepancy was explored using a combination of finite-element calculation and diffusion coefficient calculation.

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Section: Introductionmentioning

confidence: 99%

Dependence of microstructural evolution on the geometric structure for serviced DZ125 turbine blades

Xie

Zhao

et al. 2023

Front. Mater.

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“…The microstructures of the blade materials are degraded during the service under the coupling effect of temperature and stress, including the evolution of the morphology of the γ′ precipitates and defects (Agudo Jácome et al, 2014;Gan et al, 2020;He et al, 2021) as well as transformation of carbides and precipitation of a topological close-packed phase (TCP) (Zhang et al, 2020). At present, the research on the turbine blades mainly focuses on the relationship among the microstructure (Link et al, 2011;Dubiel and Czyrska-Filemonowicz, 2012;Avila-Davila et al, 2018), service environment (Aurrecoechea et al, 1991;Miura et al, 2010;Chen et al, 2016a;Huang et al, 2018;Fu et al, 2020) and material properties (Fu et al, 2019;Huang et al, 2019;Ren et al, 2021) of the blade.…”

Section: Introductionmentioning

confidence: 99%

Microstructure degradation of service-exposed turbine blades made of directionally solidified DZ125 superalloy

et al. 2022

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The investigation about the degradation behavior of turbine blades exposed to complex and extreme environments for long-term service is of great importance to assess the remaining life of the blades. In our work, the microstructure at different positions of the service-exposed turbine blade was characterized from the micron scale to the nanoscale. The results showed that there are noticeable differences in the microstructure at different positions of the blade and the blade has a complex service history. These conclusions suggest that the most severely damaged part of the blade should be responsible for assessing the remaining life of the blade, moreover, the mechanical properties of materials should not be limited to life at constant temperature and stress, rather non-isothermal and variable stress tests are more instructive in assessing the performance or life of aircraft engine blade materials.

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“…Its research and development and manufacturing level is an important reflection of national core competitiveness to measure national economic development and national defense security. The single crystal superalloy produced by directional solidification has excellent fatigue resistance [4][5][6] and good high-temperature mechanical properties [7,8], and its most important microstructure is composed of γ phase and γ' precipitated phase [9,10]. The γ' phases are dispersedly distributed in the γ matrix.…”

Section: Introductionmentioning

confidence: 99%

Quantitative Characterization of the γ’ Phase Distribution in the Large-Scale Area of the Second-Generation Nickel-Based Single Crystal Blade DD5

Wan

Zhou

et al. 2021

Crystals

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Nickel-based single crystal superalloy blades have excellent high-temperature performance as the hot end part of the aero-engine turbine. The most important strengthening phase in the single crystal blade is the γ’ phase, and its morphology and size distribution directly affect the high temperature performance of the single crystal blade. In this work, scanning electron microscopy (SEM) was used to obtain the microscopic images of the γ’ phase in multiple large continuous fields of view in the transverse sections of single crystal blades, and the quantitative statistical characterization of the γ’ phase was performed by image segmentation method based on deep learning. The 20 μm × 20 μm region was selected from the primary dendrite arm, the secondary dendrite arm, and the interdendrite to statistically analyze the γ’ phases. The statistical results show that the average size of the γ’ phase at the position of the interdendrite is significantly larger than the average size of the γ’ phase at the position of the dendrite; the sizes of the γ’ phase at the primary dendrite arm, the secondary dendrite arm and the interdendrite all obey the normal distribution; about 3.17 × 107 γ’ phases are counted in 20 positions in the 5 transverse sections of the single crystal blade in a total area of 5 mm2, and the size, geometric morphology and area fraction of all γ’ phases are respectively counted. In this work, the quantitative parameters of the γ’ phases at 4 different positions of the section of the single crystal superalloy DD5 blade were compared, the size and area fraction of the γ’ phases at the leading edge and the trailing edge were smaller, and the shape of the γ’ phase of the leading edge and the trailing edge is closer to the cube.

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Influence of microstructure degradation induced by pretreatment on the creep behavior in Ni-based single-crystal superalloy with different orientations

Abstract: Abstract

Cited by 7 publications

References 40 publications

Dependence of microstructural evolution on the geometric structure for serviced DZ125 turbine blades

Dependence of microstructural evolution on the geometric structure for serviced DZ125 turbine blades

Microstructure degradation of service-exposed turbine blades made of directionally solidified DZ125 superalloy

Quantitative Characterization of the γ’ Phase Distribution in the Large-Scale Area of the Second-Generation Nickel-Based Single Crystal Blade DD5

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