Structure and mechanical properties of TiZr binary alloy after Al addition

Jiang, Xiaoxiang; Jing, Ran; Liu, C.Y.; Ma, Mingzhen; Liu, R.P.

doi:10.1016/j.msea.2013.08.029

Cited by 44 publications

(11 citation statements)

References 22 publications

(21 reference statements)

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“…All ingots were turned and re-melted at least six times to ensure compositional homogeneity. The weight of alloy ingots was approximately 90 g to 100 g. The ingots were heated to 870°C for 30 min, and then rolled into plated samples with a thickness of 5 mm [5,20]. The ingots were water quenched immediately after rolling.…”

Section: Methodsmentioning

confidence: 99%

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Microstructure and mechanical properties of hot-rolled Zr–3Al–χBe alloys

Feng

Xia

Zhou

et al. 2015

Materials Science and Engineering: A

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Section: Methodsmentioning

confidence: 99%

“…Thus, the solubility of the Al element was relatively large in the Zr-based alloy. Jiang et al [20] reported that TiZrAl alloys exhibit single α phase with 15 at% (7.28 wt%) Al added. However, the pattern showed several small peaks near 28°, 30°, and 38°after Be addition (Fig.…”

Section: Microstructure Evolutionmentioning

confidence: 99%

Microstructure and mechanical properties of hot-rolled Zr–3Al–χBe alloys

Feng

Xia

Zhou

et al. 2015

Materials Science and Engineering: A

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“…The results are not completely satisfying because the achievement of some advantages is often accompanied by drawbacks. For instance, Jiang et al [82] modified the composition of a Ti-25Zr alloy by adding Al up to 15% and found that the YS increase is accompanied by a reduction of ductility.…”

Section: α-Timentioning

confidence: 99%

Alloys for Aeronautic Applications: State of the Art and Perspectives

Gloria

Montanari

Richetta

et al. 2019

Metals

155

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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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“…The experimental results indicated that the Zr-Ti alloys possess better hardness and bending strength than pure Zr. Jiang et al [14] found that adding aluminum (Al) strongly affects the mechanical properties of Ti-Zr-Al alloys. Strength evidently increased with increasing Al contents.…”

Section: Introductionmentioning

confidence: 99%