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Introduction to life modeling of thermal barrier coatings
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Miller, R. A. |
| Copyright Year | 1984 |
| Description | Thermal barrier coatings may be applied to air-cooled turbine section airfoils to insulate such components from hot gases in the engine. The coatings, which typically consist of about 0.01 to 0.04 cm of zirconia-yttria ceramic over about 0.01 cm of NiCrAlY or NiCrAlZr alloy bond coat, allow increased gas temperatures or reduced cooling air flows. This, in turn, leads to marked improvements in engine efficiency and performance. However, certain risks are associated with designing for maximum benefits, and eventually a point is reached where coating loss would immediately jeopardize the underlying component. Therefore, designers must be able to accurately predict the life of a given bill-of-material coating in any particular design. The results of an in-house aeronautics, base research and technology program which is designed to provide the first steps towards developing mission-capable life-prediction models are outlined. |
| File Size | 238634 |
| Page Count | 5 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19870001762 |
| Archival Resource Key | ark:/13960/t4zh1gc2t |
| Language | English |
| Publisher Date | 1984-10-01 |
| Access Restriction | Open |
| Subject Keyword | Nonmetallic Materials Air Flow Thermal Control Coatings Exhaust Gases Life Durability Morphology Failure Modes Mathematical Models High Temperature Prediction Analysis Techniques Turbine Engines Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
