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Thermal-structural mission analyses of air-cooled gas turbine blades
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Kaufman, A. Gaugler, R. E. |
| Copyright Year | 1978 |
| Description | Cyclic temperature and stress-strain states in cooled turbine blades were calculated for a simulated mission of an advanced technology aircraft engine. TACT1 (three dimensional heat transfer) and MARC (nonlinear structural analysis) computer programs were used to analyze impingement cooled airfoils, with and without leading-edge film cooling. Creep was the predominant damage mode, particularly around film cooling holes. Radially angled holes exhibited less creep than holes normal to surface. Beam-type analyses of all-impingement cooled airfoils gave fair agreement with MARC results for initial creep. |
| File Size | 1279478 |
| Page Count | 13 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19790003262 |
| Archival Resource Key | ark:/13960/t3809wn0s |
| Language | English |
| Publisher Date | 1978-01-01 |
| Access Restriction | Open |
| Subject Keyword | Structural Mechanics Air Cooling Gas Turbines Stress-strain Relationships Turbine Blades Fatigue Materials Gas Turbine Engines Airfoils Aircraft Engines Film Cooling Computer Programs Creep Analysis Structural Analysis Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
