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Design, fabrication and spin testing of ceramic blade metal disk attachmentA ceramic turbine blade-metal disk attachment was designed for small, non man-rated turbine engine applications. The selected design consisted of a hot pressed silicon nitride blade having a skewed dovetail attachment with a compliant interlayer between the disk and the blade. Two-dimensional and three-dimensional analyses predicted that life goals could be achieved, considering both NDE limitations and crack growth rates for the ceramic material. Twenty ceramic blades were fabricated to closely-held manufacturing tolerances. New fracture mechanics data at elevated temperature are presented.
Document ID
19790009686
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Calvert, G. (Pratt and Whitney Aircraft Group West Palm Beach, FL, United States)
Date Acquired
September 3, 2013
Publication Date
February 1, 1979
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NASA-CR-159532
FR-10179
Accession Number
79N17857
Funding Number(s)
CONTRACT_GRANT: NAS3-19715
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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