Film cooling effectiveness on the suction side of a turbine blade in a two dimensional laminar flow /
The study of film cooling effectiveness on the suction side of a CF6-50 model turbine using numerical method. The study is limited to two dimensional laminar flow with asumption og incompressible flow, adiabatic condition and govern by steady-state form of governing equation. The result of film cool...
| Үндсэн зохиолч: | |
|---|---|
| Формат: | |
| Хэвлэсэн: |
Sekudai : UTM,
1994
|
| Нөхцлүүд: |
| Тойм: | The study of film cooling effectiveness on the suction side of a CF6-50 model turbine using numerical method. The study is limited to two dimensional laminar flow with asumption og incompressible flow, adiabatic condition and govern by steady-state form of governing equation. The result of film cooling effectiveness were calculated along down stream of the a single injection hole located 25 percent of the suction surface. The injection angle use were30 and 35 degree with blowing ratio of M+0.1,0.5 and 0.8. The result of the study shows that the film cooling effectiveness on the suction side (vonvex side) of the model turbine increases with decreasing injection angle, andincreased blowing ratio. The film cooling effectiveness is at it highestin the immediate down stream region of the injection hole and decreases down stream from the injection hole. |
|---|