| Autor: |
Bharathkumar, H., Jensin Joshua, J., Devi, P. Booma, Raja Joseph, D. |
| Zdroj: |
International Journal of Ambient Energy; November 2019, Vol. 40 Issue: 8 p832-837, 6p |
| Abstrakt: |
The maximum operating temperature of a steam turbine is restricted to 600°C due to its corrosive nature, whereas the gas turbine inlet temperature can be increased up to 1500°C. The film cooling is one of the widely employed methods to cool the aircraft turbine blades. The cooling passages are generally formed using the laser drilling process and the re-solidification of the molten metal takes place at local cold spots. Thus, the imperfection is formed in the coolant passage, which affects the flow characteristics and hence the effectiveness of the film cooling reduces. In the present work, the effect of the imperfection on the various flow parameters is investigated. A flat plate with the film cooling hole attached beneath at a distance of 0.1 m from the leading edge of the plate is investigated and it was found that the imperfection reduces the effectiveness by 32%. |
| Databáze: |
Supplemental Index |
| Externí odkaz: |
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