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Record Details

Record 27 of 4084
Turbine blade nonlinear structural and life analysis
Author and Affiliation:
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)
Abstract: The 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.
Publication Date: Jun 01, 1982
Document ID:
19820051446
(Acquired Nov 30, 1995)
Accession Number: 82A34981
Subject Category: AIRCRAFT PROPULSION AND POWER
Report/Patent Number: AIAA PAPER 82-1056
Document Type: Conference Paper
Publisher Information: United States
Meeting Information: Joint Propulsion Conference; 18th; June 21-23, 1982; Cleveland, OH
Meeting Sponsor: AIAA, SAE, and ASME
Financial Sponsor: NASA; United States
Organization Source: General Electric Co.; Cincinnati, OH, United States
NASA Lewis Research Center; Cleveland, OH, United States
Description: 9p; In English
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: Copyright
NASA Terms: BLADE TIPS; CRACK INITIATION; FATIGUE LIFE; PREDICTION ANALYSIS TECHNIQUES; STRESS ANALYSIS; STRUCTURAL FAILURE; TURBINE BLADES; AXIAL STRAIN; CREEP PROPERTIES; GAS TURBINE ENGINES; HIGH TEMPERATURE TESTS; ISOPARAMETRIC FINITE ELEMENTS; STRESS CYCLES; STRESS RELAXATION; STRESS-STRAIN RELATIONSHIPS
Imprint And Other Notes: AIAA, SAE, and ASME, Joint Propulsion Conference, 18th, Cleveland, OH, June 21-23, 1982, AIAA 9 p.
Availability Source: Other Sources
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