Loading...
Please wait, while we are loading the content...
Similarity tests of turbine vanes, effects of ceramic thermal barrier coatings
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Gladden, H. J. |
| Copyright Year | 1980 |
| Description | The role of material thermal conductivity was analyzed for its effect on the thermal performance of air-cooled gas turbine components coated with a ceramic thermal barrier material when tested at reduced temperatures and pressures. It is shown that the thermal performance can be evaluated reliably at reduced gas and coolant conditions; however, thermal conductivity corrections are required for the data at reduced conditions. Corrections for a ceramic thermal barrier coated vane are significantly different than for an uncoated vane. Comparison of uncorrected test data, therefore, would show erroneously that the thermal barrier coating was ineffective. When thermal conductivity corrections are applied to the test data these data are then shown to be representative of engine data and also show that the thermal barrier coating increases the vane cooling effectiveness by 12.5 percent. |
| File Size | 718835 |
| Page Count | 14 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19800013220 |
| Archival Resource Key | ark:/13960/t8qc4ts40 |
| Language | English |
| Publisher Date | 1980-01-01 |
| Access Restriction | Open |
| Subject Keyword | Fluid Mechanics And Heat Transfer Analogies Thermal Control Coatings Turbine Blades Ceramic Coatings Gas Turbine Engines Vanes Yttrium Alloys Thermal Conductivity Heat Transfer Zirconium Alloys Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
