Abstract
The combustion instability phenomenon in the gas turbine engines brings out elevated vibrations under high temperature levels. The present work addresses the projection of a life assessment methodology applied in a laboratory-scaled generic combustor onto the typical gas turbine engine combustor section in terms of crack and its evaluation. A temperature-structural analysis based on the combustion experiments was utilized to obtain the crack initiation region. Sequentially coupled extended finite element method (XFEM) based fracture mechanics analysis was performed to characterize the crack-tip near fields in a typical combustor nickel-based superalloy.
| Original language | English |
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| Title of host publication | Proceedings of the 28th Congress of the International Council of the Aeronautical Sciences (ICAS 2012) |
| Editors | I Grant |
| Place of Publication | Brisbane, Australia |
| Publisher | International Council of the Aeronautical Sciences (ICAS) |
| Pages | 4.2.2- |
| Number of pages | 10 |
| ISBN (Print) | 978-0-9565333-1-9 |
| Publication status | Published - 23 Sept 2012 |
| Event | 28th Congress of the International Council of the Aeronautical Sciences, ICAS 2012 - Brisbane, Australia Duration: 23 Sept 2012 → 28 Sept 2012 Conference number: 28 |
Conference
| Conference | 28th Congress of the International Council of the Aeronautical Sciences, ICAS 2012 |
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| Abbreviated title | ICAS |
| Country/Territory | Australia |
| City | Brisbane |
| Period | 23/09/12 → 28/09/12 |
Keywords
- IR-81141
- METIS-287679