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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
19760042909
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Kaufman, A. (NASA Lewis Research Center Cleveland, Ohio, United States)
Date Acquired
August 8, 2013
Publication Date
March 1, 1976
Subject Category
Aircraft Propulsion And Power
Meeting Information
Meeting: Gas Turbine Conference and Products Show
Location: New Orleans, LA
Start Date: March 21, 1976
End Date: March 25, 1976
Sponsors: American Society of Mechanical Engineers
Accession Number
76A25875
Distribution Limits
Public
Copyright
Other

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