Turbine airfoil vane with an impingement insert having a plurality of impingement nozzles

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;
• and
• a 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;
• and
• a 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.

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;
• and
• a 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;
• and
• a 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.