Quantification of the influence of increased pre-stretching on microstructure-strength relationships in the Al–Cu–Li alloy AA2195

Rodgers, Benjamin; Prangnell, P.B.

doi:10.1016/j.actamat.2016.02.017

Cited by 307 publications

(52 citation statements)

References 48 publications

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“…The stretching of a tapered plate leads to a strain gradient, and it is necessary to know the maximum strain that can be achieved without fracture. Recently, Rodgers and Prangnell [30] have investigated the effect of increasing the pre-stretching of the Al-Cu-Li alloy AA2195 to higher levels than those currently used in industrial practice, focussing the attention on the behavior of the T 1 phase. At the maximum pre-strain level before plastic instability (15%), YS increased to~670 MPa and ductility decreased to 7.5% in the T8 condition.…”

Section: Al-li Alloysmentioning

confidence: 99%

Alloys for Aeronautic Applications: State of the Art and Perspectives

Gloria

Montanari

Richetta

et al. 2019

Metals

148

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In recent years, a great effort has been devoted to developing a new generation of materials for aeronautic applications. The driving force behind this effort is the reduction of costs, by extending the service life of aircraft parts (structural and engine components) and increasing fuel efficiency, load capacity and flight range. The present paper examines the most important classes of metallic materials including Al alloys, Ti alloys, Mg alloys, steels, Ni superalloys and metal matrix composites (MMC), with the scope to provide an overview of recent advancements and to highlight current problems and perspectives related to metals for aeronautics. Horizontal stabilizersLower Compression CYS, E, DT Upper Tension DT, YS As shown in Figure 2, engines consist of cold (fan, compressor and casing) and hot (combustion chamber and turbine) sections. The material choice depends on the working temperature. The components of cold sections require materials with high specific strength and corrosion resistance. Ti and Al alloys are very good for these applications. For instance, the working temperature of the compressor is in the range of 500-600 °C, and the Ti-6Al-2Sn-4Zr-6Mo alloy (YS = 640 MPa at 450 °C; excellent corrosion resistance) is the most commonly used material.For the hot sections, materials with good creep resistance, mechanical properties at high temperature and high-temperature corrosion resistance are required, and Ni-base superalloys are the optimal choice.

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Section: Al-li Alloysmentioning

confidence: 99%

Alloys for Aeronautic Applications: State of the Art and Perspectives

Gloria

Montanari

Richetta

et al. 2019

Metals

148

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“…The basis that creep strain rates of all specimens treated by pre-stretching in the first stage are lower than that of un-stretched sample can be explained by two facts. One is that the pre-stretching treatment introduces many kinds of defects such as dislocations and vacancies in the matrix [15], which act as strong obstacles to the dislocation movements, leading to the precipitation of the second phase. Meanwhile, the work hardening caused by the pre-stretching facilitates the accumulation of internal dislocation resulting in the generation of creep strain is hindered by more deposits [16].…”

Section: Effect Of Pre-stretching On the Creep And Mechanical Propertmentioning

confidence: 99%

Effect of Pre-Stretching on Microstructures and Mechanical Behaviors of Creep-Aged 7055 Al Alloy and Its Constitutive Modeling

Zuo

Cao

et al. 2019

Metals

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The rational pre-stretching can contribute to obtaining better mechanical properties. This paper studies the effect of creep stain, mechanical properties, and microstructures of 7055 alloy under different pre-stretching conditions. The results show that compared with solid-quenched alloy, the 7055-T6 alloy is the optimal scheme to attain more creep strain, and the range of pre-stretching from 1.6% to 3.3% is suitable for creep-aged 7055-T6 alloy to obtain better mechanical properties. Further examination by TEM test shows that pre-stretching promotes the formation of dislocations, which provides superior nucleation regions for ή phase resulting in a higher strength alloy. Meanwhile, a unified creep-aging constitutive model for 7055-T6 alloy is established which can be used to accurately predict its creep behavior under the different pre-stretching.

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“…There are several ways to measure the volume fraction of the precipitates in alloys (Chen et al, 2013;Donnadieu et al, 2011;Rodgers and Prangnell, 2016). In our work, d ifferential scanning calorimeter (DSC) was used to quantify the relative volu me fract ions (RVF) of the different type precipitates (Rodgers and Prangnell, 2016). The volu me proportion of θ" to θ' can be determined with the statistical analysis in S/TEM images, i.e.…”

Section: Relative Volume Fractionmentioning

confidence: 99%

Stress-level-dependent microstructure evolution and deformation behaviors during creep age forming of AA2219 alloy

Zhan

Liu

et al. 2018

MATEC Web Conf.

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Creep age forming (CAF) can shape and strengthen the sheet metals loaded externally at elevated temperature by corresponding creep/stress-relaxation and age hardening. Understanding the deformation and strengthening behavior at different stress levels plays a pivotal role in accurate prediction of CAF. This work experimentally investigates the effect of stress level on the evolution of both properties and microstructures, including precipitates and dislocations, during CAF. The microstructural evolution is characterized in detail by scanning/transmission electron microscopy (S/TEM) and X-ray diffraction (XRD). Stress orienting effect of θ» occurs at low-stress loaded samples and results in a decline in the hardening potential of creep-aging. A bimodal distribution of precipitates consisted of θ» homogeneously formed in the matrix and θ' heterogeneously formed on dislocations is found in the high-stress loaded samples, giving rise to a significant enhancement of hardening response. In addition, the creep strain increases drastically when the loading stress is higher than the initial yield strength. The relevant mechanisms for the transition of the obtained strength and creep behaviors with the applied stress are discussed based on microstructure observations.

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Quantification of the influence of increased pre-stretching on microstructure-strength relationships in the Al–Cu–Li alloy AA2195

Cited by 307 publications

References 48 publications

Alloys for Aeronautic Applications: State of the Art and Perspectives

Alloys for Aeronautic Applications: State of the Art and Perspectives

Effect of Pre-Stretching on Microstructures and Mechanical Behaviors of Creep-Aged 7055 Al Alloy and Its Constitutive Modeling

Stress-level-dependent microstructure evolution and deformation behaviors during creep age forming of AA2219 alloy

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