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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 (α), compound angle (β ), 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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Publisher copy:
10.1115/GT2011-45721

Authors


Ireland, P More by this author
Volume:
5
Issue:
PARTS A AND B
Pages:
353-367
Publication date:
2011
DOI:
URN:
uuid:ce6d85f7-934e-4b1a-b7b3-4a304bb69503
Source identifiers:
396446
Local pid:
pubs:396446
ISBN:
9780791854655

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