Details
| Original language | English |
|---|---|
| Pages (from-to) | 3-14 |
| Number of pages | 12 |
| Journal | Materials at high temperatures |
| Volume | 15 |
| Issue number | 1 |
| Publication status | Published - 1998 |
| Externally published | Yes |
Abstract
The development of high-temperature titanium alloys has been dominated by the requirements of aerospace industries. Initially, improvements in tensile strength and creep properties were the main interest. Gas inlet temperatures in aero-engines have increased continuously and, nowadays certain components in gas turbine engines that are made out of titanium alloys, such as compressor discs and rotor blades, approach operating temperatures as high as 550°C. As a result of alloy development, near-α alloys capable of operating temperatures up to 600°C are commercially available. These alloys are intended to partially replace heavier nickel-base superalloys, e.g. in the compressor of gas turbine engines and much work has been directed towards understanding high-temperature fatigue, creep-fatigue interaction and oxidation behaviour of titanium alloys. It has been recognized that alloy composition, heat treatment and microstructure all influence strongly the high-temperature properties of titanium alloys. This review focusses on the relationship between microstructure and high-temperature fatigue behaviour of titanium alloys. It will cover mainly conventional (α + β) alloys and near-α alloys which have been optimized with respect to both creep and high-temperature fatigue properties.
Keywords
- Creep-fatigue, Environmental degradation, High-temperature fatigue, Microstructure, Oxidation, Thermomechanical fatigue, Titanium alloys
ASJC Scopus subject areas
- Materials Science(all)
- Ceramics and Composites
- Physics and Astronomy(all)
- Condensed Matter Physics
- Engineering(all)
- Mechanics of Materials
- Engineering(all)
- Mechanical Engineering
- Materials Science(all)
- Metals and Alloys
- Materials Science(all)
- Materials Chemistry
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In: Materials at high temperatures, Vol. 15, No. 1, 1998, p. 3-14.
Research output: Contribution to journal › Article › Research › peer review
}
TY - JOUR
T1 - High-temperature fatigue of titanium alloys
AU - Maier, H. J.
PY - 1998
Y1 - 1998
N2 - The development of high-temperature titanium alloys has been dominated by the requirements of aerospace industries. Initially, improvements in tensile strength and creep properties were the main interest. Gas inlet temperatures in aero-engines have increased continuously and, nowadays certain components in gas turbine engines that are made out of titanium alloys, such as compressor discs and rotor blades, approach operating temperatures as high as 550°C. As a result of alloy development, near-α alloys capable of operating temperatures up to 600°C are commercially available. These alloys are intended to partially replace heavier nickel-base superalloys, e.g. in the compressor of gas turbine engines and much work has been directed towards understanding high-temperature fatigue, creep-fatigue interaction and oxidation behaviour of titanium alloys. It has been recognized that alloy composition, heat treatment and microstructure all influence strongly the high-temperature properties of titanium alloys. This review focusses on the relationship between microstructure and high-temperature fatigue behaviour of titanium alloys. It will cover mainly conventional (α + β) alloys and near-α alloys which have been optimized with respect to both creep and high-temperature fatigue properties.
AB - The development of high-temperature titanium alloys has been dominated by the requirements of aerospace industries. Initially, improvements in tensile strength and creep properties were the main interest. Gas inlet temperatures in aero-engines have increased continuously and, nowadays certain components in gas turbine engines that are made out of titanium alloys, such as compressor discs and rotor blades, approach operating temperatures as high as 550°C. As a result of alloy development, near-α alloys capable of operating temperatures up to 600°C are commercially available. These alloys are intended to partially replace heavier nickel-base superalloys, e.g. in the compressor of gas turbine engines and much work has been directed towards understanding high-temperature fatigue, creep-fatigue interaction and oxidation behaviour of titanium alloys. It has been recognized that alloy composition, heat treatment and microstructure all influence strongly the high-temperature properties of titanium alloys. This review focusses on the relationship between microstructure and high-temperature fatigue behaviour of titanium alloys. It will cover mainly conventional (α + β) alloys and near-α alloys which have been optimized with respect to both creep and high-temperature fatigue properties.
KW - Creep-fatigue
KW - Environmental degradation
KW - High-temperature fatigue
KW - Microstructure
KW - Oxidation
KW - Thermomechanical fatigue
KW - Titanium alloys
UR - http://www.scopus.com/inward/record.url?scp=0031650333&partnerID=8YFLogxK
U2 - 10.1080/09603409.1998.11689571
DO - 10.1080/09603409.1998.11689571
M3 - Article
AN - SCOPUS:0031650333
VL - 15
SP - 3
EP - 14
JO - Materials at high temperatures
JF - Materials at high temperatures
SN - 0960-3409
IS - 1
ER -