NDLI: Thermal fatigue durability for advanced propulsion materials

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Thermal fatigue durability for advanced propulsion materials

Content Provider	NASA Technical Reports Server (NTRS)
Author	Halford, Gary R.
Copyright Year	1989
Description	A review is presented of thermal and thermomechanical fatigue (TMF) crack initiation life prediction and cyclic constitutive modeling efforts sponsored recently by the NASA Lewis Research Center in support of advanced aeronautical propulsion research. A brief description is provided of the more significant material durability models that were created to describe TMF fatigue resistance of both isotropic and anisotropic superalloys, with and without oxidation resistant coatings. The two most significant crack initiation models are the cyclic damage accumulation model and the total strain version of strainrange partitioning. Unified viscoplastic cyclic constitutive models are also described. A troika of industry, university, and government research organizations contributed to the generation of these analytic models. Based upon current capabilities and established requirements, an attempt is made to project which TMF research activities most likely will impact future generation propulsion systems.
File Size	815377
Page Count	13
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19900005325
Archival Resource Key	ark:/13960/t1bk68h48
Language	English
Publisher Date	1989-10-01
Access Restriction	Open
Subject Keyword	Structural Mechanics Thermodynamics Fatigue Life Partitions Mathematics Heat Resistant Alloys Viscoplasticity Thermal Fatigue Mathematical Models Prediction Analysis Techniques Spacecraft Construction Materials Turbine Engines Crack Initiation 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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