- 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...
Expand abstract - Publisher copy:
- 10.1115/GT2011-45721
-
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- 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
- Copyright date:
- 2011
Conference
Influence of film cooling hole angles and geometries on aerodynamic loss and net heat flux reduction
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