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Turbine blade temperature measurements using thin film temperature sensors
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Grant, H. P. Claing, R. G. Przybyszewski, J. S. |
| Copyright Year | 1981 |
| Description | 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. |
| File Size | 3740977 |
| Page Count | 61 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19810010750 |
| Archival Resource Key | ark:/13960/t5q864g14 |
| Language | English |
| Publisher Date | 1981-03-17 |
| Access Restriction | Open |
| Subject Keyword | Metallic Materials Turbine Blades Metal Bonding Calibrating Thermocouples Adhesion Tests Wire Adhesion Sputtering Thin Films Temperature Sensors Temperature Measurement Rhodium Platinum Oxidation Combustion Chambers Vibration Tests Aluminum Oxides Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
