| 摘要 |
An airfoil for a combustion turbine comprising a leading edge, a trailing edge, and an airfoil portion defined therebetween is provided. The airfoil has an axial chord length. The suction side of the airfoil portion has an accelerating flow section which is formed such that a gas flow continues to accelerate for over more than one half of the axial chord length such that a flow boundary layer remains substantially attached along the decelerating section of the airfoil even if film cooling fluid is ejected. |
