Turbine airfoil vane with an impingement insert having a plurality of impingement nozzles
View Patent ↗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.
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; 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, 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; 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.
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; 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.
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.