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- W776970211 abstract "This work is motivated by the need to accurately predict heat transfer in turbomachinery. For efficient gas turbine operation, flow temperatures in the hot gas path exceed acceptable metal temperatures in many regions of the engine. So that the integrity of the parts can be maintained for an acceptable engine life, the parts must be cooled. Efficient cooling schemes require accurate heat transfer prediction to minimize regions that are overcooled and, even more importantly, to ensure adequate cooling in high-heat-flux regions." @default.
- W776970211 created "2016-06-24" @default.
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- W776970211 date "2003-03-01" @default.
- W776970211 modified "2023-09-24" @default.
- W776970211 title "Glenn-HT Code Validated for Complex Turbine Blade Cooling Passage" @default.
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- W776970211 hasPublicationYear "2003" @default.
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