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Turbine blade tip durability analysisAn air-cooled turbine blade from an aircraft gas turbine engine chosen for its history of cracking was subjected to advanced analytical and life-prediction techniques. The utility of advanced structural analysis techniques and advanced life-prediction techniques in the life assessment of hot section components are verified. Three dimensional heat transfer and stress analyses were applied to the turbine blade mission cycle and the results were input into advanced life-prediction theories. Shortcut analytical techniques were developed. The proposed life-prediction theories are evaluated.
Document ID
19810018554
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Mcknight, R. L. (General Electric Co. Cincinnati, OH, United States)
Laflen, J. H. (General Electric Co. Cincinnati, OH, United States)
Spamer, G. T. (General Electric Co. Cincinnati, OH, United States)
Date Acquired
September 4, 2013
Publication Date
February 1, 1981
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NASA-CR-165268
R81AEG372
Report Number: NASA-CR-165268
Report Number: R81AEG372
Accession Number
81N27092
Funding Number(s)
PROJECT: RTOP 505-33-82
CONTRACT_GRANT: NAS3-22020
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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