| DOI | Trouver le DOI : https://doi.org/10.1115/GT2016-56120 |
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| Auteur | Rechercher : Wu, Xijia1; Rechercher : Zhang, Zhong1; Rechercher : Jiang, Leiyong1; Rechercher : Patnaik, Prakash1 |
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| Affiliation | - Conseil national de recherches du Canada. Aérospatiale
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| Format | Texte, Article |
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| Conférence | ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition, June 13-17, 2016, Seoul, South Korea |
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| Résumé | Nozzle guide vanes (NGV) of gas turbine engines are the first components to withstand the impingement of hot combustion gas, and therefore often suffer thermal fatigue failures in service. A lifing analysis is performed for the NGV of a gas turbine engine using the integrated creep-fatigue theory (ICFT). With the constitutive formulation of inelastic strain in terms of mechanism-strain components such as rate-independent plasticity, dislocation glide-plus-climb, and grain boundary sliding, the dominant deformation mechanisms at the critical locations are thus identified quantitatively with the corresponding mechanism-strain component. The material selection scenarios are discussed with regards to damage accumulated during take-off and cruise. The interplay of those deformation mechanisms in the failure process are elucidated such that an “optimum” material selection solution may be achieved. |
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| Date de publication | 2016-06-13 |
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| Maison d’édition | The American Society Mechanical Engineers |
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| Dans | |
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| Série | |
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| Langue | anglais |
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| Publications évaluées par des pairs | Oui |
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| Numéro NPARC | 23001202 |
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| Exporter la notice | Exporter en format RIS |
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| Signaler une correction | Signaler une correction (s'ouvre dans un nouvel onglet) |
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| Identificateur de l’enregistrement | 353db729-39f0-4052-81c2-c71f84988690 |
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| Enregistrement créé | 2017-01-05 |
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| Enregistrement modifié | 2021-08-13 |
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