Turbine blade temperature measurements using thin film temperature sensors

Technical Report · Sun Mar 01 04:00:00 EST 1981

OSTI ID:5757424

Grant, H P; Przybyszewski, J S; Claing, R G

The 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.

• Research Organization: Pratt and Whitney Aircraft, East Hartford, CT (USA)
• OSTI ID: 5757424
• Report Number(s): NASA-CR-165201
• Country of Publication: United States
• Language: English

Related Subjects

33 ADVANCED PROPULSION SYSTEMS
330103* -- Internal Combustion Engines-- Turbine
ALUMINIUM COMPOUNDS
ALUMINIUM OXIDES
CALIBRATION
CHALCOGENIDES
COMBUSTORS
DEPOSITION
ENGINES
FABRICATION
FAILURES
GAS TURBINE ENGINES
HEAT ENGINES
INTERNAL COMBUSTION ENGINES
OXIDES
OXYGEN COMPOUNDS
SPUTTERING
SURFACE COATING
TEMPERATURE MEASUREMENT
TURBINE BLADES