| 摘要 |
A turbine airfoil, such as a turbine blade, having a showerhead for cooling the leading edge region. A plurality of rows of exit film slots are arranged along the leading edge in the spanwise direction and staggered from each other. The exit slots are connected to narrow cooling air passages formed within the airfoil wall in which a plurality of rows of micro pin fins extend across the passage to form serpentine flow paths for the cooling air. Cooling air from a cooling air supply channel is metered into an impingement cavity to produce backside impingement cooling of the leading edge wall. The cooling air is diffused and then passed into the plurality of narrow cooling air passages to be metered again and serpentine flow through the narrow passages, and then diffused into the exit film slots. The cooling air is then ejected from the diffusion slots as a film layer of cooling air onto the leading edge airfoil surface. The narrows cooling air passages with the micro pin fins can also be arranged on the pressure side or the suction side walls of the airfoil to provide improved impingement and diffusion and film cooling for the airfoil surface.
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