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Thermal-barrier-coated turbine blade studyThe effects of coating TBC on a CF6-50 stage 2 high-pressure turbine blade were analyzed with respect to changes in the mean bulk temperature, cooling air requirements, and high-cycle fatigue. Localized spallation was found to have a possible deleterious effect on low-cycle fatigue life. New blade design concepts were developed to take optimum advantage of TBCs. Process and material development work and rig evaluations were undertaken which identified the most promising combination as ZrO2 containing 8 w/o Y2O3 applied by air plasma spray onto a Ni22Cr-10Al-1Y bond layer. The bond layer was applied by a low-pressure, high-velocity plasma spray process onto the base alloy. During the initial startup cycles the blades experienced localized leading edge spallation caused by foreign objects.
Document ID
19820002167
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Siemers, P. A.
(General Electric Co. Saint Petersburg, FL, United States)
Hillig, W. B.
(General Electric Co. Saint Petersburg, FL, United States)
Date Acquired
September 4, 2013
Publication Date
August 1, 1981
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
SRD-81-083
NASA-CR-165351
Accession Number
82N10040
Funding Number(s)
CONTRACT_GRANT: NAS3-21727
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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