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A turbine vane includes a generally elongated hollow airfoil and a cooling system. The cooling system is positioned within the airfoil and includes a cooling chamber and an impingement insert positioned in the cooling chamber. The impingement insert and an inner surface of an outer wall of the airfo

A turbine vane includes a generally elongated hollow airfoil and a cooling system. The cooling system is positioned within the airfoil and includes a cooling chamber and an impingement insert positioned in the cooling chamber. The impingement insert and an inner surface of an outer wall of the airfoil define a cooling channel therebetween. The impingement insert includes a plurality of impingement nozzles extending toward the inner surface of the outer wall and a plurality of impingement orifices. At least one of the impingement orifices is arranged in a non-aligned pattern with respect to at least one adjacent impingement orifice such that cooling fluid passing out of the at least one impingement orifice does not directly flow into a centerline of a cooling fluid flowpath of cooling fluid passing out of the at least one adjacent impingement orifice.

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1. A turbine vane, comprising: a generally elongated hollow airfoil comprising an outer wall, the outer wall including a leading edge, a trailing edge, a pressure side, a suction side, an outer endwall at a first end, and an inner endwall at a second end opposite the first end; anda cooling system p

1. A turbine vane, comprising: a generally elongated hollow airfoil comprising an outer wall, the outer wall including a leading edge, a trailing edge, a pressure side, a suction side, an outer endwall at a first end, and an inner endwall at a second end opposite the first end; anda cooling system positioned within the airfoil, the cooling system comprising a cooling chamber and an impingement insert positioned in the cooling chamber, the impingement insert and an inner surface of the airfoil outer wall defining a cooling channel therebetween, the impingement insert including: a plurality of impingement nozzles extending toward the inner surface of the outer wall; anda plurality of impingement orifices, at least one of the impingement orifices being arranged in a non-aligned pattern with respect to at least one adjacent impingement orifice such that cooling fluid passing out of the at least one impingement orifice does not directly flow into a centerline of a cooling fluid flowpath of cooling fluid passing out of the at least one adjacent impingement orifice, to reduce disruption of a post impingement cooling fluid flowing normal to impinging jets flowing out of the impingement orifices within the cooling channel. 2. The turbine vane of claim 1, wherein each impingement orifice is arranged in a non-aligned pattern with respect to at least one adjacent impingement orifice such that cooling fluid passing out of each impingement orifice does not directly flow into a centerline of a cooling fluid flowpath of cooling fluid passing out of the at least one adjacent impingement orifice. 3. The turbine vane of claim 2, wherein the orifices are arranged in a staggered pattern comprising alternating first and second rows that are offset from one another in a flow direction of cooling fluid through the cooling channel. 4. The turbine vane of claim 1, wherein each of the impingement orifices is formed in an outermost aspect of a corresponding impingement nozzle. 5. The turbine vane of claim 4, wherein the impingement nozzles have a generally cylindrical cross sectional area. 6. The turbine vane of claim 4, wherein each impingement nozzle includes at least one impingement orifice for directing cooling fluids orthogonally away from the impingement insert. 7. The turbine vane of claim 4, wherein a distance between the outermost aspect of the impingement nozzle and the inner surface of the outer wall is less than half of a distance between an innermost aspect of the impingement insert and the inner surface of the outer wall. 8. The turbine vane of claim 1, wherein only select ones of the impingement nozzles include a corresponding impingement orifice formed therein. 9. A turbine vane, comprising: a generally elongated hollow airfoil comprising an outer wall, the outer wall including a leading edge, a trailing edge, a pressure side, a suction side, an outer endwall at a first end, and an inner endwall at a second end opposite the first end; anda cooling system positioned within the airfoil, the cooling system comprising a cooling chamber and an impingement insert positioned in the cooling chamber, the impingement insert and an inner surface of the airfoil outer wall defining a cooling channel therebetween, the impingement insert including: a plurality of impingement nozzles extending toward the inner surface of the outer wall; anda plurality of impingement orifices arranged in a staggered pattern comprising alternating first and second rows that are offset from one another in a flow direction of cooling fluid through the cooling channel such that cooling fluid passing out of each respective impingement orifice does not directly flow into a centerline of a cooling fluid flowpath of cooling fluid passing out of the adjacent upstream impingement orifice, to reduce disruption of a post impingement cooling fluid flowing normal to impinging jets flowing out of the impingement orifices within the cooling channel. 10. The turbine vane of claim 9, wherein each of the impingement orifices is formed in an outermost aspect of a corresponding impingement nozzle. 11. The turbine vane of claim 10, wherein only select ones of the impingement nozzles include a corresponding impingement orifice formed therein. 12. The turbine vane of claim 10, wherein the impingement nozzles have a generally cylindrical cross sectional area. 13. The turbine vane of claim 10, wherein each impingement nozzle includes at least one impingement orifice for directing cooling fluids orthogonally away from the impingement insert. 14. The turbine vane of claim 10, wherein a distance between the outermost aspect of the impingement nozzle and the inner surface of the outer wall is less than half of a distance between an innermost aspect of the impingement insert and the inner surface of the outer wall. 15. A turbine vane, comprising: a generally elongated hollow airfoil comprising an outer wall, the outer wall including a leading edge, a trailing edge, a pressure side, a suction side, an outer endwall at a first end, and an inner endwall at a second end opposite the first end; anda cooling system positioned within the airfoil, the cooling system comprising a cooling chamber and an impingement insert positioned in the cooling chamber, the impingement insert and an inner surface of the airfoil outer wall defining a cooling channel therebetween, the impingement insert including: a plurality of impingement nozzles extending toward the inner surface of the outer wall; anda plurality of impingement orifices formed in corresponding impingement nozzles and being arranged in a non-aligned pattern with respect to at least one adjacent impingement orifice such that cooling fluid passing out of the impingement orifices does not directly flow into a centerline of a cooling fluid flowpath of cooling fluid passing out of the at least one adjacent impingement orifice, wherein a distance between an outermost aspect of at least one impingement nozzle including an impingement orifice and the inner surface of the outer wall is less than half of a distance between an innermost aspect of the impingement insert and the inner surface of the outer wall, to reduce disruption of a post impingement cooling fluid flowing normal to impinging jets flowing out of the impingement orifices within the cooling channel. 16. The turbine vane of claim 15, wherein the orifices are arranged in a staggered pattern comprising alternating first and second rows that are offset from one another in a flow direction of cooling fluid through the cooling channel. 17. The turbine vane of claim 15, wherein each impingement nozzle includes at least one impingement orifice for directing cooling fluids orthogonally away from the impingement insert. 18. The turbine vane of claim 17, wherein the impingement nozzles have a generally cylindrical cross sectional area. 19. The turbine vane of claim 17, wherein each of the impingement orifices is formed in an outermost aspect of a corresponding impingement nozzle.