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An airfoil includes a leading edge, a trailing edge region, a suction surface, a pressure surface, a cooling passageway, and a column of flow separators. The suction surface and the pressure surface both extend axially between the leading edge and the trailing edge region, as well as radially from a

An airfoil includes a leading edge, a trailing edge region, a suction surface, a pressure surface, a cooling passageway, and a column of flow separators. The suction surface and the pressure surface both extend axially between the leading edge and the trailing edge region, as well as radially from a root section of the airfoil to a tip section of the airfoil to define a central cavity of the airfoil. The cooling passageway is located within the central cavity at the trailing edge region. The column of flow separators is located in the cooling passageway adjacent the trailing edge and includes a first flow separator having a first longitudinal axis and a second flow separator having a second longitudinal axis. The first longitudinal axis is offset at an angle with respect to the first longitudinal axis.

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1. An airfoil comprising: a leading edge and a trailing edge region, the trailing edge region located axially downstream from the leading edge and terminating in a trailing edge;a suction surface and a pressure surface, the suction surface and the pressure surface both extending axially between the

1. An airfoil comprising: a leading edge and a trailing edge region, the trailing edge region located axially downstream from the leading edge and terminating in a trailing edge;a suction surface and a pressure surface, the suction surface and the pressure surface both extending axially between the leading edge and the trailing edge region, as well as radially from a root section of the airfoil to a tip section of the airfoil to define a central cavity of the airfoil;a cooling passageway located within the central cavity at the trailing edge region; anda column of flow separators located in the cooling passageway adjacent the trailing edge, the column of flow separators comprising: a first flow separator having a first longitudinal axis;a second flow separator having a second longitudinal axis, wherein the first longitudinal axis is offset at an angle between 1 and 15 degrees with respect to the second longitudinal axis;a third flow separator having a third longitudinal axis, wherein the second longitudinal axis and the third longitudinal axis are substantially parallel to one another;a first cooling slot located between the first flow separator and the tip section, wherein the first cooling slot has a diffusion angle less than 20 degrees;a second cooling slot located between the second flow separator and the first flow separator, wherein the second cooling slot has a diffusion angle less than 15 degrees; anda third cooling slot located between the third flow separator and the second flow separator, wherein the third cooling slot has a diffusion angle less than or equal to 10 degrees. 2. The airfoil of claim 1, wherein the first longitudinal axis is offset at an angle of 6 degrees with respect to the second longitudinal axis. 3. The airfoil of claim 1, wherein the airfoil is a blade. 4. The airfoil of claim 1, wherein the airfoil is a vane. 5. An airfoil for a gas turbine engine, the component comprising: an airfoil including a convex surface and a concave surface, both the convex surface and the concave surface extending radially from a root section to a tip section and axially from a leading edge to a trailing edge section, the trailing edge section terminating in a trailing edge having a cut-back on the concave surface;an internal chamber defined between the convex surface and the concave surface, the internal chamber including an axially extending cooling air passageway, the cooling air passageway having a plurality of radially spaced cooling air slots terminating in outlets at the trailing edge;a column of teardrop features located in the cooling air passageway, the column of teardrop features including: a first teardrop spaced from the tip section by a first cooling air slot, the first cooling air slot having a first diffusion angle;a second teardrop spaced radially from the first teardrop by a second cooling air slot, the second cooling air slot having a second diffusion angle smaller than the first diffusion angle;a third teardrop spaced radially from the second teardrop by a third cooling air slot, the third cooling air slot having a third diffusion angle smaller than the second diffusion angle, wherein the third teardrop and the second teardrop extend parallel to one another and the first teardrop is oriented at an angle relative to the second teardrop; anda radial column of generally cylindrical pedestals extending through the cooling air passageway from the convex surface to the concave surface and located upstream of the column of teardrop features. 6. The airfoil of claim 5, wherein the airfoil is a blade. 7. The airfoil of claim 5, wherein the airfoil is a vane. 8. An airfoil for a gas turbine engine, the airfoil comprising: a leading edge and a trailing edge, the leading edge and the trailing edge both extending from a root section to a tip section;a pressure surface and a suction surface, the pressure surface and the suction surface both extending between the leading edge and the trailing edge, as well as between the root section and the tip section, the pressure surface and the suction surface defining a hollow center;a cooling passageway extending through the hollow center, the cooling passageway including cooling slots terminating with outlets at the trailing edge;a first flow separator located within the cooling passageway adjacent the trailing edge and spaced from the tip section by a first cooling slot, the first flow separator including a first rounded upstream end, a first outer wall, and a first inner wall, the first outer wall and first inner wall converging at a first downstream end, a first longitudinal axis extending through the first flow separator from the first rounded upstream end to the first downstream end, wherein the first longitudinal axis is angled so that the first downstream end is closer to the tip section than the first rounded upstream end;a second flow separator spaced radially from the first flow separator by a second cooling slot, the second flow separator including a second rounded upstream end, a second outer wall, and a second inner wall, the second outer wall and second inner wall converging at a second downstream end, a second longitudinal axis extending through the second flow separator from the second rounded upstream end to the second downstream end, wherein the first longitudinal axis is angled with respect to the second longitudinal axis; anda third flow separator spaced radially from the second flow separator by a third cooling slot, the third flow separator including a third rounded upstream end, a third outer wall, and a third inner wall, the third outer wall and third inner wall converging at a third downstream end, a third longitudinal axis extending through the third flow separator from the third rounded upstream end to the third downstream end, wherein the third longitudinal axis is substantially parallel to the second longitudinal axis. 9. The airfoil of claim 8, wherein the airfoil is a blade. 10. The airfoil of claim 8, wherein the airfoil is a vane.