| DOI | Resolve DOI: https://doi.org/10.1115/GT2016-56120 |
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| Author | Search for: Wu, Xijia1; Search for: Zhang, Zhong1; Search for: Jiang, Leiyong1; Search for: Patnaik, Prakash1 |
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| Affiliation | - National Research Council of Canada. Aerospace
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| Format | Text, Article |
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| Conference | ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition, June 13-17, 2016, Seoul, South Korea |
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| Abstract | 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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| Publication date | 2016-06-13 |
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| Publisher | The American Society Mechanical Engineers |
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| In | |
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| Series | |
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| Language | English |
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| Peer reviewed | Yes |
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| NPARC number | 23001202 |
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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 | 353db729-39f0-4052-81c2-c71f84988690 |
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| Record created | 2017-01-05 |
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| Record modified | 2021-08-13 |
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