Film cooling adiabatic effectiveness measurements of pressure side trailing edge cooling configurations
Nowadays total inlet temperature of gas turbine is far above the permissible metal temperature; as a consequence, advanced cooling techniques must be applied to protect from thermal stresses, oxidation and corrosion the components located in the high pressure stages, such as the blade trailing edge....
| Main Authors: | , , , , , |
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| Format: | Article |
| Language: | English |
| Published: |
Elsevier
2015-12-01
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| Series: | Propulsion and Power Research |
| Subjects: | |
| Online Access: | http://www.sciencedirect.com/science/article/pii/S2212540X15000619 |