Conference item
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...
Expand abstract
Actions
Authors
Bibliographic Details
- Volume:
- 5
- Issue:
- PARTS A AND B
- Pages:
- 353-367
- Host title:
- Proceedings of the ASME Turbo Expo
- Publication date:
- 2011-01-01
- DOI:
- Source identifiers:
-
396446
- ISBN:
- 9780791854655
Item Description
- Pubs id:
-
pubs:396446
- UUID:
-
uuid:ce6d85f7-934e-4b1a-b7b3-4a304bb69503
- Local pid:
- pubs:396446
- Deposit date:
- 2013-11-17
Terms of use
- Copyright date:
- 2011
If you are the owner of this record, you can report an update to it here: Report update to this record