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Internal coating of air-cooled gas turbine bladesFour modified aluminide coatings were developed for IN-792 + Hf alloy using a powder pack method applicable to internal surfaces of air-cooled blades. The coating compositions are Ni-19Al-1Cb, Ni-19Al-3Cb, Ni-17Al-20Cr, and Ni-12Al-20Cr. Cyclic burner rig hot corrosion (900 C) and oxidation (1050 C) tests indicated that Ni-Al-Cb coatings provided better overall resistance than Ni-Al-Cr coatings. Tensile properties of Ni-19Al-1Cb and Ni-12Al-20Cr coated test bars were fully retained at room temperature and 649 C. Stress rupture results exhibited wide scatter around uncoated IN-792 baseline, especially at high stress levels. High cycle fatigue lives of Ni-19Al-1Cb and Ni-12Al-20Cr coated bars (as well as RT-22B coated IN-792) suffered approximately 30 percent decrease at 649 C. Since all test bars were fully heat treated after coating, the effects of coating/processing on IN-792 alloy were not recoverable. Internally coated Ni-19Al-1Cb, Ni-19Al-3Cb, and Ni-12Al-20Cr blades were included in 500-hour endurance engine test and the results were similar to those obtained in burner rig oxidation testing.
Document ID
19810015533
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Hsu, L. L. (Solar Turbines Inc. San Diego, CA, United States)
Stetson, A. R. (Solar Turbines Inc. San Diego, CA, United States)
Date Acquired
September 4, 2013
Publication Date
December 1, 1980
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NASA-CR-165337
SRBI-R-4828-16
Accession Number
81N24068
Funding Number(s)
PROJECT: RTOP 505-01-12
CONTRACT_GRANT: NAS3-28142
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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