Abstract
Numerical simulation and experiment were carried out to study the characteristics of different cooling configurations in a typical low pressure turbine blade. Numerical simulations were performed to investigate the heat transfer of original blade and the improved blade. The numerical results show a good agreement with the experimental ones. Compared to the original blade, the improved blade enhanced the heat transfer effectiveness about 7.8%. The research results indicate that the configuration improving the inner passage not only reinforces the performance of heat transfer, but also improves temperature distribution and avoids superheated regions.
| Original language | English |
|---|---|
| Pages (from-to) | 668-672 |
| Number of pages | 5 |
| Journal | Hangkong Dongli Xuebao/Journal of Aerospace Power |
| Volume | 20 |
| Issue number | 4 |
| State | Published - Aug 2005 |
Keywords
- Aerospace propulsion system
- Gas turbine
- Heat transfer
- Pin-fin array
- Turbine blade
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