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Influence of Film Cooling Hole Angles and Geometries on Aerodynamic Loss and Net Heat Flux Reduction

Abstract:

Turbine design engineers have to ensure that film cooling can provide sufficient protection to turbine blades from the hot mainstream gas, while keeping the losses low. Film cooling hole design parameters include inclination angle (a), compound angle (b), hole inlet geometry, and hole exit geometry. The influence of these parameters on aerodynamic loss and net heat flux reduction is investigated, with loss being the primary focus. Low-speed flat plate experiments have been conducted at moment...

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Publication status:
Published

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Publisher copy:
10.1115/1.4023088
Journal:
JOURNAL OF TURBOMACHINERY-TRANSACTIONS OF THE ASME More from this journal
Volume:
135
Issue:
5
Pages:
051019-051019
Publication date:
2013-09-01
DOI:
EISSN:
1528-8900
ISSN:
0889-504X
Language:
English
Pubs id:
pubs:418121
UUID:
uuid:8d3a197c-8520-4a5a-a0cb-7e5742aae2ce
Local pid:
pubs:418121
Source identifiers:
418121
Deposit date:
2013-11-17

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