Design and Analysis of Gas Turbine Blade with Cooling
The turbine inlet temperature in advanced gas turbine engine is very high and it is above the melting point of blade material. In this project radial convective cooling method is used. The turbine blade with cooling holes (6, 8, 9,10, and 11) is designed using CATIA V5. The models are analyzed usin...
| Автори: | , |
|---|---|
| Формат: | Стаття |
| Мова: | English |
| Опубліковано: |
European Alliance for Innovation (EAI)
2018-09-01
|
| Серія: | EAI Endorsed Transactions on Energy Web |
| Предмети: | |
| Онлайн доступ: | https://publications.eai.eu/index.php/ew/article/view/964 |