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Low cost heat treatment process for production of dual microstructure superalloy disks
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Kantzos, Pete Furrer, David Gayda, John Gabb, Tim |
| Copyright Year | 2003 |
| Description | There are numerous incidents where operating conditions imposed on a component mandate different and distinct mechanical property requirements from location to location within the component. Examples include a crankshaft in an internal combustion engine, gears for an automotive transmission, and disks for a gas turbine engine. Gas turbine disks are often made from nickel-base superalloys, because these disks need to withstand the temperature and stresses involved in the gas turbine cycle. In the bore of the disk where the operating temperature is somewhat lower, the limiting material properties are often tensile and fatigue strength. In the rim of the disk, where the operating temperatures are higher than those of the bore, because of the proximity to the combustion gases, resistance to creep and crack growth are often the limiting properties. |
| File Size | 4329198 |
| Page Count | 18 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_20030022720 |
| Archival Resource Key | ark:/13960/t0qr9s146 |
| Language | English |
| Publisher Date | 2003-01-01 |
| Access Restriction | Open |
| Subject Keyword | Metals And Metallic Materials Heat Treatment Nickel Alloys Low Cost Heat Resistant Alloys Internal Combustion Engines Turbine Wheels Gas Turbine Engines Combustion Products Microstructure Tensile Strength Operating Temperature Crack Propagation 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 |
