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U.S. Department of Energy
Office of Scientific and Technical Information

Replaceable blade turbine and stationary specimen corrosion testing facility

Technical Report ·
OSTI ID:5736453
A 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.
Research Organization:
National Aeronautics and Space Administration, Cleveland, OH (USA). Lewis Research Center
OSTI ID:
5736453
Report Number(s):
N-85-18126; NASA-TM-86931; E-2371
Country of Publication:
United States
Language:
English