Evaluation of Ti-48al-2cr-2nb Under Fretting Conditions PDF Download
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Author: National Aeronautics and Space Adm Nasa
Publisher: Independently Published
ISBN: 9781726673938
Category : Science
Languages : en
Pages : 36
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Book Description
The fretting behavior of Ti-48Al-2Cr-2Nb (y-TiAl) in contact with the nickel-base superalloy 718 was examined in air at temperatures from 296 to 823 K (23 to 550 C). The interfacial adhesive bonds between Ti-48Al-2Cr-2Nb and superalloy 718 were generally stronger than the cohesive bonds within Ti-48Al-2Cr-2Nb. The failed Ti-48Al-2Cr-2Nb debris subsequently transferred to the superalloy 718. In reference experiments conducted with Ti-6Al-4V against superalloy 718 under identical fretting conditions, the degree of transfer was greater for Ti-6A1-4V than for Ti-48Al-2Cr-2Nb. Wear of Ti-48Al-2Cr-2Nb generally decreased with increasing fretting frequency. The increasing rate of oxidation at elevated temperatures led to a drop in wear at 473 K. However, fretting wear increased as the temperature was increased from 473 to 823 K. At 723 and 823 K, oxide film disruption generated cracks, loose wear debris, and pits on the Ti-48Al-2Cr-2Nb wear surface. Both increasing slip amplitude and increasing load tended to produce more metallic wear debris, causing severe abrasive wear in the contacting metals. Miyoshi, Kazuhisa and Lerch, Bradley A. and Draper, Susan L. and Raj, Sai V. Glenn Research Center NASA/TM-2001-211205, NAS 1.15:211205, ASTM-STP-1425, E-13006-1
Author: National Aeronautics and Space Adm Nasa
Publisher: Independently Published
ISBN: 9781726673938
Category : Science
Languages : en
Pages : 36
Get Book Here
Book Description
The fretting behavior of Ti-48Al-2Cr-2Nb (y-TiAl) in contact with the nickel-base superalloy 718 was examined in air at temperatures from 296 to 823 K (23 to 550 C). The interfacial adhesive bonds between Ti-48Al-2Cr-2Nb and superalloy 718 were generally stronger than the cohesive bonds within Ti-48Al-2Cr-2Nb. The failed Ti-48Al-2Cr-2Nb debris subsequently transferred to the superalloy 718. In reference experiments conducted with Ti-6Al-4V against superalloy 718 under identical fretting conditions, the degree of transfer was greater for Ti-6A1-4V than for Ti-48Al-2Cr-2Nb. Wear of Ti-48Al-2Cr-2Nb generally decreased with increasing fretting frequency. The increasing rate of oxidation at elevated temperatures led to a drop in wear at 473 K. However, fretting wear increased as the temperature was increased from 473 to 823 K. At 723 and 823 K, oxide film disruption generated cracks, loose wear debris, and pits on the Ti-48Al-2Cr-2Nb wear surface. Both increasing slip amplitude and increasing load tended to produce more metallic wear debris, causing severe abrasive wear in the contacting metals. Miyoshi, Kazuhisa and Lerch, Bradley A. and Draper, Susan L. and Raj, Sai V. Glenn Research Center NASA/TM-2001-211205, NAS 1.15:211205, ASTM-STP-1425, E-13006-1
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 22
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Book Description
Author: SV. Raj
Publisher:
ISBN:
Category : Fatigue
Languages : en
Pages : 15
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Book Description
The fretting behavior of Ti-48Al-2Cr-2Nb2 (?-TiAl) in contact with a typical nickel-base superalloy was examined in air at temperatures from 296 to 823 K (23 to 550 °C). The interfacial adhesive bonds between Ti-48Al-2Cr-2Nb and superalloy were generally stronger than the cohesive bonds within Ti-48Al-2Cr-2Nb. The failed Ti-48Al-2Cr-2Nb debris subsequently transferred to the superalloy. In reference experiments conducted with Ti-6Al-4V against superalloy under identical fretting conditions, the degree of transfer was greater for Ti-6Al-4V than for Ti-48Al-2Cr-2Nb. Wear of Ti-48Al-2Cr-2Nb generally decreased with increasing fretting frequency. The increasing rate of oxidation at elevated temperatures led to a drop in wear at 473 K. However, fretting wear increased as the temperature was increased from 473 to 823 K. At 723 and 823 K, oxide film disruption generated cracks, loose wear debris, and pits on the Ti-48Al-2Cr-2Nb wear surface. Both increasing slip amplitude and increasing load tended to produce more metallic wear debris, causing severe abrasive wear in the contacting metals.
Author: Steven E. Kinyon
Publisher: ASTM International
ISBN: 0803134568
Category : Contact mechanics
Languages : en
Pages : 445
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Book Description
Contains 29 contributions drawn from the Third International Symposium on Fretting Fatigue held in Nagaoka, Japan in May 2001. Sections of the volume address fretting wear and crack initiation; fretting fatigue crack and damage; life prediction; fretting fatigue parameter effects; loading condition
Author:
Publisher: DIANE Publishing
ISBN: 1428918213
Category :
Languages : en
Pages : 251
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Book Description
Author:
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 636
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 250
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Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781721138197
Category :
Languages : en
Pages : 138
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Book Description
Gamma TiAl was evaluated as a candidate alloy for low-pressure turbine blades in aeroengines. The durability of g-TiAl was studied by examining the effects of impact or fretting on its fatigue strength. Cast-to-size Ti-48Al-2Cr-2Nb was studied in impact testing with different size projectiles at various impact energies as the reference alloy and subsequently fatigue tested. Impacting degraded the residual fatigue life. However, under the ballistic impact conditions studied, it was concluded that the impacts expected in an aeroengine would not result in catastrophic damage, nor would the damage be severe enough to result in a fatigue failure under the anticipated design loads. In addition, other gamma alloys were investigated including another cast-to-size alloy, several cast and machined specimens, and a forged alloy. Within this Ti-48-2-2 family of alloys aluminum content was also varied. The cracking patterns as a result of impacting were documented and correlated with impact variables. The cracking type and severity was reasonably predicted using finite element models. Mean stress affects were also studied on impact-damaged fatigue samples. The fatigue strength was accurately predicted based on the flaw size using a threshold-based, fracture mechanics approach. To study the effects of wear due to potential applications in a blade-disk dovetail arrangement, the machined Ti-47-2-2 alloy was fretted against In-718 using pin-on-disk experiments. Wear mechanisms were documented and compared to those of Ti-6Al-4V. A few fatigue samples were also fretted and subsequently fatigue tested. It was found that under the conditions studied, the fretting was not severe enough to affect the fatigue strength of g-TiAl. Draper, Susan L. and Lerch, Bradley A. and Pereira, J. Michael and Miyoshi, Kazuhisa and Arya, Vinod K. and Zhuang, Wyman Glenn Research Center WBS 22-708-24-06
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Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1044
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Author: Hanshan Dong
Publisher: Elsevier
ISBN: 1845699459
Category : Technology & Engineering
Languages : en
Pages : 681
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Book Description
The growing use of light alloys in industries such as aerospace, sports equipment and biomedical devices is driving research into surface engineering technologies to enhance their properties for the desired end use. Surface engineering of light alloys: Aluminium, magnesium and titanium alloys provides a comprehensive review of the latest technologies for modifying the surfaces of light alloys to improve their corrosion, wear and tribological properties. Part one discusses surface degradation of light alloys with chapters on corrosion behaviour of magnesium alloys and protection techniques, wear properties of aluminium-based alloys and tribological behaviour of titanium alloys. Part two reviews surface engineering technologies for light alloys including anodising, plasma electrolytic oxidation, thermal spraying, cold spraying, physical vapour deposition, plasma assisted surface treatment, PIII/PSII treatments, laser surface modification, ceramic conversion and duplex treatments. Part three covers applications for surface engineered light alloys including sports equipment, biomedical devices and plasma electrolytic oxidation and anodised aluminium alloys for spacecraft applications. With its distinguished editor and international team of contributors, Surface engineering of light alloys: Aluminium, magnesium and titanium alloys is a standard reference for engineers, metallurgists and materials scientists looking for a comprehensive source of information on surface engineering of aluminium, magnesium and titanium alloys. Discusses surface degradation of light alloys considering corrosion behaviour and wear and tribological properties Examines surface engineering technologies and modification featuring plasma electrolytic oxidation treatments and both thermal and cold spraying Reviews applications for engineered light alloys in sports equipment, biomedical devices and spacecraft
