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Grainex mar-m 247 turbine disk life study for nasa's high temperature high speed turbine seal test facility
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Delgado, Irebert R. |
| Copyright Year | 2015 |
| Description | An experimental and analytical fatigue life study was performed on the Grainex Mar-M 247 disk used in NASA s Turbine Seal Test Facility. To preclude fatigue cracks from growing to critical size in the NASA disk bolt holes due to cyclic loading at severe test conditions, a retirement-for-cause methodology was adopted to detect and monitor cracks within the bolt holes using eddy-current inspection. For the NASA disk material that was tested, the fatigue strain-life to crack initiation at a total strain of 0.5 percent, a minimum to maximum strain ratio of 0, and a bolt hole temperature of 649 C was calculated to be 665 cycles using -99.95 percent prediction intervals. The fatigue crack propagation life was calculated to be 367 cycles after implementing a safety factor of 2 on life. Thus, the NASA disk bolt hole total life or retirement life was determined to be 1032 cycles at a crack depth of 0.501 mm. An initial NASA disk bolt hole inspection at 665 cycles is suggested with 50 cycle inspection intervals thereafter to monitor fatigue crack growth. |
| File Size | 93955552 |
| Page Count | 244 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_20050239002 |
| Archival Resource Key | ark:/13960/t40s4s522 |
| Language | English |
| Publisher Date | 2015-04-01 |
| Access Restriction | Open |
| Subject Keyword | Metals And Metallic Materials Cycles Fatigue Life Test Facilities Safety Factors Cyclic Loads Inspection Turbines Holes Mechanics 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 |
