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An oxide dispersion strengthened alloy for gas turbine blades
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Glasgow, T. K. |
| Copyright Year | 1979 |
| Description | The strength of the newly developed alloy MA-6000E is derived from a nickel alloy base, an elongated grain structure, naturally occurring precipitates of gamma prime, and an artificial distribution of extremely fine, stable oxide particles. Its composition is Ni-15Cr-2Mo-2Ta-4W-4.5Al-2.5Ti-0.15Zr 0.05C-0.01B-1.1Y2O3. It exhibits the strength of a conventional nickel-base alloy at 1400 F but is quite superior at 2000 F. Its shear strength is relatively low, necessitating consideration of special joining procedures. Its high cycle, low cycle, and thermal fatigue properties are excellent. The relationship between alloy microstructure and properties is discussed. |
| File Size | 1343439 |
| Page Count | 13 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19790012009 |
| Archival Resource Key | ark:/13960/t01z90r20 |
| Language | English |
| Publisher Date | 1979-01-01 |
| Access Restriction | Open |
| Subject Keyword | Spacecraft Propulsion And Power Grain Boundaries Turbine Blades Nickel Alloys Gas Turbine Engines Oxides Thermal Fatigue Precipitates Particle Size Distribution Heat Resistant Alloys Chemical Composition High Strength Alloys Microstructure Oxide Dispersion Strengthening 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 |
