| DOI | Resolve DOI: https://doi.org/10.4224/40003731 |
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| Author | Search for: Cheng, S. M.1; Search for: Beres, W.1 |
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| Affiliation | - National Research Council Canada. NRC Institute for Aerospace Research
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| Format | Text, Technical Report |
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| Physical description | 52 p. |
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| Abstract | Stress and fracture mechanics analyses of the turbine disc in the Nene X engine (T-33 aircraft) subjected to mechanical and thermal loading were carried out using the finite element method. In both stress and fracture mechanics analyses, two- and threedimensional finite element models were constructed. The stress distribution obtained from the uncracked disc established the fracture critical location at the center of the first tooth root of the firtree. In fracture mechanics calculations stress intensity factors were obtained for through-the-thickness andpart-through-the-thickness cracks 4 mm and 8mm in depth with aspect ratios of 1.5 and 2.25 embedded in fracture critical location. The calculation results provided the basis for the prediction of safe inspection intervals for the Nene X turbine discs. |
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| Publication date | 1998-06 |
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| Publisher | National Research Council Canada |
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| Series | |
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| Note | The content is temporarily unavailable |
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| Language | English |
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| Peer reviewed | No |
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| NRC number | SMPL-1999-0026 |
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| NPARC number | 8931824 |
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| Export citation | Export as RIS |
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| Report a correction | Report a correction (opens in a new tab) |
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| Record identifier | 082364a9-d412-4ca7-ab84-7c562031e20d |
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| Record created | 2009-04-23 |
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| Record modified | 2025-11-26 |
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