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Turbine Blade Temperature Measurements Using Thin Film Temperature SensorsThe development of thin film temperature sensors is discussed. The technology for sputtering 2 micron thin film platinum versus platinum 10 percent rhodium thermocouples on alumina forming coatings was improved and extended to applications on actual turbine blades. Good adherence was found to depend upon achieving a proper morphology of the alumina surface. Problems of adapting fabrication procedures to turbine blades were uncovered, and improvements were recommended. Testing at 1250 K at one atmosphere pressure was then extended to a higher Mach No. (0.5) in combustor flow for 60 hours and 71 thermal cycles. The mean time to failure was 47 hours accumulated during 1 hour exposures in the combustor. Calibration drift was about 0.1 percent per hour, attributable to oxidation of the rhodium in the thin films. An increase in film thickness and application of a protective overcoat are recommended to reduce drift in actual engine testing.
Document ID
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Grant, H. P.
(Pratt and Whitney Aircraft Group East Hartford, CT, United States)
Przybyszewski, J. S.
(Pratt and Whitney Aircraft Group East Hartford, CT, United States)
Claing, R. G.
(Pratt and Whitney Aircraft Group East Hartford, CT, United States)
Date Acquired
September 4, 2013
Publication Date
March 17, 1981
Subject Category
Metallic Materials
Report/Patent Number
Accession Number
Funding Number(s)
Distribution Limits
Work of the US Gov. Public Use Permitted.
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