Abstract
Different types of ribs, protrusions and dimples were installed on the target surface with impingement cooling in order to improve the cooling performance of the turbine vane with limited influence on the coolant consumption. Conjugate heat transfer was adopted to analyze the influence of different turbulators on the internal heat transfer and discharge coefficient of jet and film holes in real working conditions. Then the overall cooling performance was obtained and optimization thoughts was summarized, which serves as guidance for the vane design. The results show that, the introduction of cooling structure can hinder the development of cross flow, increase the discharge coefficient of impingement holes and enhance the disturbance of the flow field, thus enhance the internal heat transfer, whereas, the external film cooling deteriorates for the reason of decreasing discharge coefficient of film holes. The combined effect of the enhancement of internal heat transfer and the weakening of external film cooling reduces the outer wall temperature of the vane. Through optimization, the effect of rib is stronger than that of the dimples or protrusions, when arranged them between the ribs help to further strengthen the heat transfer. The orthogonal rib+dimple structure mostly increases the overall cooling efficiency by 1.96%~4.09% while reducing the consumption of cooling air by 1.19%~1.81%, so is the optimal structure.
| Translated title of the contribution | Numerical Study on Flow and Heat Transfer Characteristics of Internal Cooling Configurations of Turbine Vane |
|---|---|
| Original language | Chinese (Traditional) |
| Article number | 210551 |
| Journal | Tuijin Jishu/Journal of Propulsion Technology |
| Volume | 43 |
| Issue number | 12 |
| DOIs | |
| State | Published - Dec 2022 |