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Replaceable blade turbine and stationary specimen corrosion testing facilityA facility was constructed to provide relatively low cost testing of hot section turbine blade and vane materials under hot corrosion conditions more akin to service environments. The facility consists of a small combustor whose pressurized gas flow can be directed to either a test section consisting of three small cascaded specimens or to a partial admittance single-stage axial flow turbine. The turbine rotor contains 28 replaceable turbine blades. The combustion gases resulting from the burning of Jet A-l fuel can be seeded with measured amounts of alkali salts. This facility is described here along with preliminary corrosion test results obtained during the final checkout of the facility.
Document ID
Document Type
Technical Memorandum (TM)
Santoro, G. J.
(NASA Lewis Research Center Cleveland, OH, United States)
Calfo, F. D.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 5, 2013
Publication Date
January 1, 1985
Subject Category
Metallic Materials
Report/Patent Number
NAS 1.15:86931
Accession Number
Funding Number(s)
PROJECT: RTOP 533-04-12
Distribution Limits
Work of the US Gov. Public Use Permitted.
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