“…Since the spur gears of the scaled gearbox have a surface layer and therefore partly hardened and partly unhardened material, the fracture locus cannot be determined based on tensile, shear, and compression tests. Referring to the paper of Ghazali et al [27], the applicability of a simple shift of the fracture locus, caused by the heat treatment of the material, is reviewed. As there were only plastic deformations and no initial cracks in the quasi-static ingestion tests on the scaled gearbox, only the pulsator test and the FIT can be used for determination and validation.…”
Section: Determine the Fracture Locus Of The Layered Materials Modelmentioning
confidence: 99%
“…In addition to the dependence on the stress state, Ghazali et al [27] report a dependence of the heat treatment on the failure parameters. Regarding Ghazali, heat-treated specimens have a downwards-shifted fracture locus (Figure 1).…”
Before a new type of engine is introduced into civil aviation, it must comply with various safety regulations. These regulations include the analysis of secondary damage caused by the re-ingestion of a tooth fragment. The purpose is to prevent crack propagation through the gear rim, which would lead to catastrophic failure. In this context, identification of the initial crack location is crucial to determine the crack propagation path. Therefore, this paper presents a technique to determine and validate a constitutive material model and fracture locus for case-hardened spur gears. As the modelling of the surface-hardened layer is computationally intensive, it is necessary to homogenise the model. This paper comprehensively reviews and discusses the associated effects and errors. To determine the plastic behaviour of the case-hardened external gear (30CrNiMo8) and the nitrided internal gear (35CrAlNi7-10), the widely acknowledged Johnson–Cook material model is implemented using compression and Vickers indenter tests to define the necessary parameters. The fracture locus implementation is also based on the Johnson–Cook method and an axial shift of the fracture locus based on the hardness profile of the spur gears is determined by quasi-static pulsator tests. For validation, a project-specific gearbox test rig is used, enabling consistent ingestion of defined fragments. In addition, to check the likelihood of a tooth flank crack and to validate the results, a simplified ingestion experiment is performed.
“…Since the spur gears of the scaled gearbox have a surface layer and therefore partly hardened and partly unhardened material, the fracture locus cannot be determined based on tensile, shear, and compression tests. Referring to the paper of Ghazali et al [27], the applicability of a simple shift of the fracture locus, caused by the heat treatment of the material, is reviewed. As there were only plastic deformations and no initial cracks in the quasi-static ingestion tests on the scaled gearbox, only the pulsator test and the FIT can be used for determination and validation.…”
Section: Determine the Fracture Locus Of The Layered Materials Modelmentioning
confidence: 99%
“…In addition to the dependence on the stress state, Ghazali et al [27] report a dependence of the heat treatment on the failure parameters. Regarding Ghazali, heat-treated specimens have a downwards-shifted fracture locus (Figure 1).…”
Before a new type of engine is introduced into civil aviation, it must comply with various safety regulations. These regulations include the analysis of secondary damage caused by the re-ingestion of a tooth fragment. The purpose is to prevent crack propagation through the gear rim, which would lead to catastrophic failure. In this context, identification of the initial crack location is crucial to determine the crack propagation path. Therefore, this paper presents a technique to determine and validate a constitutive material model and fracture locus for case-hardened spur gears. As the modelling of the surface-hardened layer is computationally intensive, it is necessary to homogenise the model. This paper comprehensively reviews and discusses the associated effects and errors. To determine the plastic behaviour of the case-hardened external gear (30CrNiMo8) and the nitrided internal gear (35CrAlNi7-10), the widely acknowledged Johnson–Cook material model is implemented using compression and Vickers indenter tests to define the necessary parameters. The fracture locus implementation is also based on the Johnson–Cook method and an axial shift of the fracture locus based on the hardness profile of the spur gears is determined by quasi-static pulsator tests. For validation, a project-specific gearbox test rig is used, enabling consistent ingestion of defined fragments. In addition, to check the likelihood of a tooth flank crack and to validate the results, a simplified ingestion experiment is performed.
“…The failure rate through the material is high as it is easily affected by corrosion. The steel alloy AISI4340 is a medium carbon steel that offers high tensile strength and appreciable resistance to corrosion [6] . However, this material has poor weldability as associated with spatter and high slag formation [ 3 , 6 ].…”
Section: Data Descriptionmentioning
confidence: 99%
“…The steel alloy AISI4340 is a medium carbon steel that offers high tensile strength and appreciable resistance to corrosion [6] . However, this material has poor weldability as associated with spatter and high slag formation [ 3 , 6 ]. The high spatter in welding AISI4340 yields porosity, incomplete fusion, and shallow penetration defects.…”
“…In contrast, at high cooling rates, a complete transformation of austenite into martensite is obtained, increasing the mechanical properties. However, it is also known that this transformation can lead to a higher magnitude of residual stresses and increase the probability of distortion and fracture failures in the pieces [6][7][8][9]. Jami et al [10] analyzed the behavior of the torsional strength and hardness of an AISI 4340 steel after quenching and tempering, using an austenitizing temperature of 860 • C and tempering temperatures of 300 • C, 350 • C, and 400 • C for a soaking time of 120 min.…”
Although quenching is one of the most widely used heat treatments in the metal-mechanical industry to improve the mechanical properties of steels, it is also responsible for the generation of residual stress, distortion, and fractures in the treated parts. The high-temperature gradients present during quenching and martensitic transformation are the main failure mechanisms. Cooling is the critical quenching stage where several variables that need to be controlled are involved in reducing these problems. The objective of this research was to evaluate the main variables in the quenching process in SAE 4340 steels, which promote distortion, residual stress accumulation, and fracture failures. A 2ᴷ factorial experiment was designed, samples with C-ring geometry susceptible to changes in quenching variables were used, and the variables studied were the agitation and temperature of the quenching medium. Experimental measurements, statistical tools and modeling were used to evaluate and predict the distortion generated in quenched samples. Such tools include Minitab 21® software and its statistics utilities. Furthermore, a finite element method model was carried out using STFC Deform®. The results suggest that there are optimal conditions in the quenching process to minimize distortion and residual stresses and to improve mechanical properties of quenched parts; therefore, the methods used in this work could be useful to detect and control the appearance of defects in an industrial environment.
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