| 摘要 |
<p>A turbine airfoil incorporates a film cooling arrangement composed of a plurality of multi-outlet holes defined through the opposite side walls to permit flow of cooling air from the hollow interior chamber of the airfoil to the external surface of the side walls. Each multi-outlet hole includes a flow inlet (52) at the internal surface of the side walls and communicating with the hollow interior chamber, at least a pair of flow outlets (58A,B) at the exterior surface of the side walls, and at least a pair of flow branches (64A,B) extending through the side walls and between the flow inlet and the flow outlets. The flow branches merge and intersect with one another at the flow inlet. The flow outlets are displaced preferably downstream of the flow inlet relative to the direction of gas flow past the external surface of the side walls of the airfoil. The flow branches extend through the side walls in inclined relation to the external surface of the side walls. <IMAGE></p> |
