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Advanced turbine disk designs to increase reliability of aircraft enginesResults of analytical studies to improve the low cycle fatigue lives and reliability of turbine disks in high performance gas turbine engines are presented. Advanced disk concepts were evaluated for the first stage high pressure turbines of the CF6-50 and JT8D-17 engines. The advanced disk designs are compared to the existing disks on the bases of cycles to crack initiation and overspeed capability for initially unflawed disks, crack propagation cycles to failure for initially flawed disks, and available kinetic energy of disk burst fragments.
Document ID
19760010055
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Kaufman, A. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
January 1, 1976
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
E-8491
NASA-TM-X-71804
Report Number: E-8491
Report Number: NASA-TM-X-71804
Meeting Information
Meeting: Gas Turbine Conf.
Location: New Orleans, LA
Country: United States
Start Date: March 21, 1976
End Date: March 25, 1976
Sponsors: ASME
Accession Number
76N17143
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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