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Heat transfer enhancement within a turbine blade cooling passage using ribs and combinations of ribs with film cooling holes

Abstract:

A transient heat transfer method using liquid crystals has been applied to a scale model of a turbine rotor blade passage. Detailed contours of local heat transfer coefficient are presented for the passage in which the heat transfer to one wall was enhanced first by ribs and then with ribs combined with holes. The hole geometry and experimental dimensionless flow rates were representative of those occurring at the entrance to engine film cooling holes. The results for the ribbed passage are c...

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Institution:
University of Oxford
Department:
Oxford, MPLS, Engineering Science
Role:
Author
Journal:
Journal of Turbomachinery
Volume:
118
Issue:
3
Pages:
428-434
Publication date:
1996-07-05
ISSN:
0889-504X
URN:
uuid:c00a28a9-c37b-4d93-8395-18f8aef8f516
Source identifiers:
399314
Local pid:
pubs:399314
Language:
English

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