초록

The present application provides a turbine nozzle. The turbine nozzle may include an airfoil with a leading edge and a trailing edge and a flow fence extending from the leading edge to the trailing edge.

대표청구항 ▼

1. A turbine nozzle, comprising: an airfoil;the airfoil comprising a leading edge, a trailing edge, a suction side, and a pressure side; anda flow fence extending along the suction side comprising: a first arcuate surface having a first constant radius of curvature extending from the suction side to

1. A turbine nozzle, comprising: an airfoil;the airfoil comprising a leading edge, a trailing edge, a suction side, and a pressure side; anda flow fence extending along the suction side comprising: a first arcuate surface having a first constant radius of curvature extending from the suction side towards a base of the airfoil; anda second arcuate surface extending from the suction side towards the first arcuate surface, the second arcuate surface having a second constant radius of curvature that is different than the first constant radius of curvature, wherein the first and second arcuate surfaces converge at a line, thereby forming an edge of the flow fence along the line;wherein: the flow fence extends from the leading edge to the trailing edge of the airfoil;the edge of the flow fence formed by the first and second arcuate surfaces is separated from the suction side a first distance at a position between the leading edge and the trailing edge and at a second distance at the leading edge and the trailing edge; andthe first distance is greater than the second distance;wherein the turbine nozzle is a last stage turbine nozzle. 2. The turbine nozzle of claim 1, wherein the airfoil extends from a base to a tip and wherein the flow fence is positioned adjacent to the tip. 3. The turbine nozzle of claim 1, wherein the first and second arcuate surfaces form a substantial V-like cross-sectional shape. 4. The turbine nozzle of claim 1, wherein the flow fence extends in a substantially linear direction. 5. The turbine nozzle of claim 1, wherein the flow fence comprises a uniform thickness as measured from a first intersection of the first arcuate surface and the suction side and a second intersection of the second arcuate surface and the suction side. 6. The turbine nozzle of claim 1, wherein the flow fence comprises a forward leading flow fence, wherein a forward portion of the flow fence positioned near the leading edge of the airfoil extends further from the suction side of the airfoil than a rearward portion of the flow fence positioned near the trailing edge of the airfoil. 7. The turbine nozzle of claim 1, further comprising a plurality of flow fences. 8. The turbine nozzle of claim 1, wherein the flow fence comprises a rear leading flow fence, wherein a rearward portion of the flow fence positioned near the trailing edge of the airfoil extends further from the suction side of the airfoil than a forward portion of the flow fence positioned near the leading edge of the airfoil. 9. The turbine nozzle of claim 1, wherein the flow fence is shaped to reduce flow migration in a flow of hot combustion gases along the airfoil. 10. The turbine nozzle of claim 1, wherein the flow fence is substantially parallel to a tip of the airfoil. 11. A turbine, comprising: a plurality of nozzles; anda plurality of buckets;the plurality of buckets comprising an airfoil;the airfoil comprising a suction side, a pressure side, a leading edge, a trailing edge, and a flow fence extending between the leading edge and the trailing edge;wherein the flow fence comprises: a first arcuate surface having a constant radius of curvature extending from either the suction side or the pressure side of the airfoil;a second flat surface extending from either the suction side or the pressure side of the airfoil and converging with the first arcuate surface at a line, such that the first arcuate surface and the second flat surface form an edge of the flow fence along the line of convergence;wherein the first arcuate surface is positioned closer to a tip of the airfoil than the second flat surface. 12. The turbine of claim 11, wherein the flow fence extends along the suction side of the airfoil. 13. The turbine of claim 11, wherein the flow fence extends along the pressure side of the airfoil. 14. The turbine of claim 11, further comprising a plurality of flow fences. 15. The turbine of claim 11, wherein the airfoil extends from a base to a tip and wherein the flow fence is positioned adjacent to the tip. 16. The turbine of claim 11, wherein the flow fence is shaped to reduce flow migration in a flow of hot combustion gases along the airfoil. 17. A turbine nozzle airfoil, comprising: a leading edge;a trailing edge,a pressure side;a suction side; anda flow fence extending from along a perimeter of the airfoil, wherein the flow fence comprises: a first arcuate surface having a first constant radius of curvature extending from the suction side; anda second arcuate surface extending from the suction side towards the first arcuate surface, the second arcuate surface having a second constant radius of curvature that is different than the first constant radius of curvature, wherein the first and second arcuate surfaces converge at a line, thereby forming an edge of the flow fence along the line of convergence;wherein the edge of the flow fence formed by the first and second arcuate surfaces is separated from the suction side a first distance at a first position between the leading edge and the trailing edge and is separated from the pressure side a second distance at a second position between the leading edge and the trailing edge, the first distance and the second distance being equal;the flow fence blends into the leading edge and the trailing edge; andthe turbine nozzle is a last stage turbine nozzle.