| 摘要 |
<p>Airfoil for a turbo-machine, wherein the airfoil comprises a high lift or ultra-high lift profile with a suction surface (3) having a point of minimum suction side pressure (A), a leading edge (5) and a trailing edge (6), every two adjacent airfoils form a geometric throat (2), each airfoil is provided with at least one means for reducing separation of the boundary layer on the suction surface (3), wherein the means is located longitudinally along the airfoil substantially over the entire radial length (RL) of the airfoil and comprises at least one step shaped section with at least one inner edge (24, 26) and at least one outer edge (25, 27). For providing an improved passive flow control by geometric modifications to reduce flow separation at off-design conditions, each step shaped section of the airfoil (14a, 14b) has one outer edge (25, 27) that forms a vortex shedding edge (25, 28) for a controlled generation of vortices, wherein the vortex shedding edge (25, 28) is located between 25% of the suction surface length upstream of the geometric throat (2) and 50% of the suction surface length downstream of the geometric throat (2).</p> |
