NDLI: Elevated temperature fatigue testing of metals

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Elevated temperature fatigue testing of metals

Content Provider	NASA Technical Reports Server (NTRS)
Author	Hirschberg, M. H.
Copyright Year	1981
Description	The major technology areas needed to perform a life prediction of an aircraft turbine engine hot section component are discussed and the steps required for life prediction are outlined. These include the determination of the operating environment, the calculation of the thermal and mechanical loading of the component, the cyclic stress-strain and creep behavior of the material required for structural analysis, and the structural analysis to determine the local stress-strain-temperature-time response of the material at the critical location in the components. From a knowledge of the fatigue, creep, and failure resistance of the material, a prediction of the life of the component is made. Material characterization and evaluation conducted for the purpose of calculating fatigue crack initiation lives of components operating at elevated temperatures are emphasized.
File Size	44908749
Page Count	25
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19820008545
Archival Resource Key	ark:/13960/t8nd0sd0x
Language	English
Publisher Date	1981-12-01
Access Restriction	Open
Subject Keyword	Structural Mechanics Temperature Dependence Service Life Fatigue Life Aircraft Engines Engine Parts Creep Analysis Fatigue Tests Time Dependence Stress-strain Relationships High Temperature Tests Turbine Engines Loads Forces Crack Initiation Structural Analysis Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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