Advanced Modeling Tools for Processing and Lifing of Aeroengine Components

Longuet, Arnaud; Dumont, Christian; Georges, Eric

doi:10.1007/978-3-030-51834-9_1

Cited by 8 publications

(3 citation statements)

References 41 publications

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“…Inconel 718 is a super alloy used for the manufacturing of critical rotating components in the hot sections of aero‐engines; thanks to its mechanical high performance, 1,2 such mechanical properties make it a relatively difficult material to machine 3 . Additive manufacturing (AM) is a promising technology able to print complex geometries and limiting the waste of material 4 .…”

Section: Introductionmentioning

confidence: 99%

Role of defects and microstructure on the fatigue durability of Inconel 718 obtained by additive layer manufacturing route

Sanchez‐Camargo,

Nadot,

Cormier

et al. 2023

Fatigue Fract Eng Mat Struct

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A Laser Powder Bed Fusion Inconel 718 produced with intentionally non‐optimized parameters is investigated to understand the role of defects and microstructure on the high‐cycle fatigue life. Samples from three built directions and three heat treatments were used for fatigue tests at room and 650°C under . Printing orientation has a minor effect on fatigue life at both temperatures. Most samples failed from lack of fusion defects, carefully analyzed by scanning electron microscope (SEM) observations. Surface defect leads to transgranular fracture surface, while subsurface initiation leads to crystallographic fracture surface. curves related to hot isostatic pressure condition shown that defects have higher influence at than at 650°C. Kitagawa diagrams are plotted for both temperatures to quantify the influence of defect size on fatigue limit. Natural cracks are observed at the surface in order to discuss the relative part of initiation life in the whole fatigue life.

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Section: Introductionmentioning

confidence: 99%

Role of defects and microstructure on the fatigue durability of Inconel 718 obtained by additive layer manufacturing route

Sanchez‐Camargo,

Nadot,

Cormier

et al. 2023

Fatigue Fract Eng Mat Struct

View full text Add to dashboard Cite

show abstract

“…Due to the high requirements of reliability and durability of turbine discs, creep properties of P/M superalloy are of great importance to the safety of the component [ 1 , 2 , 3 , 4 ]. Cold pre-deformation is usually used in engineering practice to control residual stress, to improve dimensional stability, and to improve the low cycle fatigue life of aero-engine discs [ 5 , 6 ]. However, pre-deformation also affects the creep properties of Ni-based superalloys at the same time, which might reduce the creep resistance of the disc material [ 7 , 8 , 9 ].…”

Section: Introductionmentioning

confidence: 99%

Experiment and Modelling of the Pre-Strain Effect on the Creep Behaviour of P/M Ni-Based Superalloy FGH96

et al. 2023

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FGH96 is a powder metallurgy Ni-based superalloy used for turbine disks of aero-engines. In the present study, room-temperature pre-tension experiments with various plastic strain were conducted for the P/M FGH96 alloy, and subsequent creep tests were conducted under the test conditions of 700 °C and 690 MPa. The microstructures of the pre-strained specimens after room-temperature pre-strain and after 70 h creep were investigated. A steady-state creep rate model was proposed, considering the micro-twinning mechanism and pre-strain effects. Progressive increases in steady-state creep rate and creep stain within 70 h were found with increasing amounts of pre-strain. Room-temperature pre-tension within 6.04% plastic strain had no obvious influence on the morphology and distribution of γ′ precipitates, although the dislocation density continuously increased with the increase in pre-strains. The increase in the density of mobile dislocations introduced by pre-strain was the main reason for the increase in creep rate. The predicted steady-state creep rates showed good agreement with the experiment data; the creep model proposed in this study could capture the pre-strain effect.

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“…Since annealing (which will introduce uneven cooling as well) cannot effectively lower the residual stresses inside the γ/γ′ alloy turbine disk, pre-spinning is usually used in industry to release and redistribute residual stress in order to obtain a better service stability and durability. It was found that the micro plastic deformation during pre-spinning can effectively lower residual stresses of the turbine disk [ 10 ], which is due to the internal stress evolution caused by the variation of interplanar spacing during deformation. Therefore, it is necessary to accurately measure the micro stress and strain during cold deformation.…”

Section: Introductionmentioning

confidence: 99%

In-Situ Synchrotron HEXRD Study on the Micro-Stress Evolution Behavior of a Superalloy during Room-Temperature Compression

et al. 2023

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The residual stress generated during heat treatment of nickel-base superalloys will affect their service performance and introduce primary cracks. In a component with high residual stress, a tiny amount of plastic deformation at room temperature can release the stress to a certain extent. However, the stress-releasing mechanism is still unclear. In the present study, the micro-mechanical behavior of the FGH96 nickel-base superalloy during room temperature compression was studied using in situ synchrotron radiation high-energy X-ray diffraction. The in situ evolution of the lattice strain was observed during deformation. The stress distribution mechanism of grains and phases with different orientations was clarified. The results show that at the elastic deformation stage, the (200) lattice plane of γ′ phase bears more stress after the stress reaches 900 MPa. When the stress exceeds 1160 MPa, the load is redistributed to the grains with their <200> crystal directions aligned with the loading direction. After yielding, the γ′ phase still bears the main stress.

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Advanced Modeling Tools for Processing and Lifing of Aeroengine Components

Cited by 8 publications

References 41 publications

Role of defects and microstructure on the fatigue durability of Inconel 718 obtained by additive layer manufacturing route

Role of defects and microstructure on the fatigue durability of Inconel 718 obtained by additive layer manufacturing route

Experiment and Modelling of the Pre-Strain Effect on the Creep Behaviour of P/M Ni-Based Superalloy FGH96

In-Situ Synchrotron HEXRD Study on the Micro-Stress Evolution Behavior of a Superalloy during Room-Temperature Compression

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