Shear creep of aircraft gas turbine alloys

In an earlier letter, observations and measurements of remarkably large shear creep at temperatures of the order of the (unofficial) target temperature of 1000K and at shear stresses close to the (unofficial) design maximum of 100 MN m exp -2 for light alloy engine components, were reported for both...

Full description

Saved in:
Bibliographic Details
Published inJournal of materials science letters Vol. 16; no. 17; pp. 1444 - 1445
Main Author ASHBEE, K. H. G
Format Journal Article
LanguageEnglish
Published Dordrecht Kluwer Academic Publishers 01.09.1997
Subjects
Applied sciences
Creep
Exact sciences and technology
Mechanical properties and methods of testing. Rheology. Fracture mechanics. Tribology
Metals. Metallurgy
Nickel base alloys
Creep
Inconel 713LC
Mechanical properties
Gas turbine
Alloy-IN-100
Aeronautic industry
Application
Velocity
Mechanism
Online AccessGet full text

Cover

More Information
Summary:In an earlier letter, observations and measurements of remarkably large shear creep at temperatures of the order of the (unofficial) target temperature of 1000K and at shear stresses close to the (unofficial) design maximum of 100 MN m exp -2 for light alloy engine components, were reported for both partially and fully lamellar alpha sub 2/ gamma titanium aluminide phase mixtures. In order to put those observations and measurements into perspective, identical shear creep tests have now been carried out on two present-generation precipitation hardened alloys, namely Inconel 713LC and IN100. Both alloys have been tested in the as-cast condition.
Bibliography:ObjectType-Article-2
SourceType-Scholarly Journals-1
ObjectType-Feature-1
content type line 23
ISSN:0261-8028
DOI:10.1023/A:1018534016060