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Turbine blade nonlinear structural and life analysisThe utility of advanced structural analysis and life prediction techniques was evaluated for the life assessment of a commercial air-cooled turbine blade with a history of tip cracking. Three dimensional, nonlinear finite element structural analyses were performed for the blade tip region. The computed strain-temperature history of the critical location was imposed on a uniaxial strain controlled test specimen to evaluate the validity of the structural analysis method. Experimental results indicated higher peak stresses and greater stress relaxation than the analytical predictions. Life predictions using the Strainrange Partitioning and Frequency Modified approaches predicted 1200 to 4420 cycles and 2700 cycles to crack initiation, respectively, compared to an observed life of 3000 cycles.
Document ID
19820051446
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Mcknight, R. L.
(General Electric Co. Cincinnati, OH, United States)
Laflen, J. H.
(General Electric Co. Cincinnati, OH, United States)
Halford, G. R.
(General Electric Co. Cincinnati, OH, United States)
Kaufman, A.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 10, 2013
Publication Date
June 1, 1982
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
AIAA PAPER 82-1056
Meeting Information
Meeting: Joint Propulsion Conference
Location: Cleveland, OH
Start Date: June 21, 1982
End Date: June 23, 1982
Sponsors: AIAA, SAE, and ASME
Accession Number
82A34981
Distribution Limits
Public
Copyright
Other

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