| 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 airfoil portion has an accelerating flow section and a decelerating flow section. The accelerating flow section 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.
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