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Aerodynamic performance of a ceramic-coated core turbine vane tested with cold air in a two-dimensional cascade
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Stabe, R. G. Liebert, C. H. |
| Copyright Year | 1975 |
| Description | The aerodynamic performance of a core turbine vane with a ceramic coating was investigated experimentally in a two-dimensional cascade of 10 vanes. The vane was first tested with a rough coating and then retested after the coating had been smoothed. The test fluid was atmospheric air. The cascade tests covered a range of pressure ratios corresponding to ideal exit critical velocity ratios of 0.6 to 0.95. The principal measurements were cross-channel surveys of exit total pressure, static pressure, and flow angle. The results presented include exit survey results and overall performance in terms of flow angle, weight flow, and kinetic energy loss. The performance of the ceramic-coated vanes is compared with the performance of an uncoated vane having a similar profile. |
| File Size | 866142 |
| Page Count | 15 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19750006652 |
| Archival Resource Key | ark:/13960/t2b901r2s |
| Language | English |
| Publisher Date | 1975-01-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Turbomachine Blades Air Cooling Cascade Flow Performance Tests Surface Properties Pressure Distribution Stator Blades Ceramics Two Dimensional Flow Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
