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 groove extending from the leading edge to the trailing edge.

대표청구항 ▼

1. A turbine nozzle, comprising: an airfoil extending from a base to a tip, wherein the tip of the airfoil is inclined along a rotor axis;the airfoil comprising a leading edge and a trailing edge; anda flow groove extending inwardly from a suction side surface of the airfoil such that the flow groov

1. A turbine nozzle, comprising: an airfoil extending from a base to a tip, wherein the tip of the airfoil is inclined along a rotor axis;the airfoil comprising a leading edge and a trailing edge; anda flow groove extending inwardly from a suction side surface of the airfoil such that the flow groove has a depth measured from the suction side surface of the airfoil, the flow groove substantially parallel to the tip of the airfoil;the flow groove extending from the leading edge to the trailing edge only along the suction side of the airfoil;wherein the flow groove blends into the suction side surface at the leading edge and the trailing edge of the airfoil, such that a first depth of the flow groove at either the leading edge or the trailing edge of the airfoil is less than a second depth of the flow groove along the side of the airfoil. 2. The turbine nozzle of claim 1, wherein the flow groove is positioned adjacent to the tip. 3. The turbine nozzle of claim 1, wherein the flow groove comprises a substantial V-like shape. 4. The turbine nozzle of claim 1, wherein the flow groove extends in a substantially linear direction. 5. The turbine nozzle of claim 1, wherein the turbine nozzle comprises a last stage nozzle. 6. The turbine nozzle of claim 1, further comprising a plurality of flow grooves. 7. The turbine nozzle of claim 1, wherein the flow groove is shaped to reduce flow migration in a flow of hot combustion gases along the airfoil. 8. A turbine, comprising: a plurality of nozzles; anda plurality of buckets;the plurality of buckets comprising an airfoil;the airfoil extending from a base to a tip, wherein the tip of the airfoil is inclined along a rotor axis, the airfoil comprising a leading edge, a trailing edge, a suction side and a flow groove extending only along the suction side of the airfoil between the leading edge and the trailing edge;wherein the flow groove extends inwardly from the suction side of the airfoil such that the flow groove has a depth measured from the suction side of the airfoil, the flow groove substantially parallel to the tip of the airfoil; andthe flow groove blends into the suction side at the leading edge and the trailing edge of the airfoil, such that a first depth of the flow groove at either the leading edge or the trailing edge of the airfoil is less than a second depth of the flow groove along the suction side of the airfoil. 9. The turbine of claim 8, wherein the flow groove is positioned adjacent to the tip. 10. The turbine of claim 8, wherein the flow groove comprises a substantial V-like shape. 11. The turbine of claim 8, wherein the flow groove extends in a substantially linear direction. 12. The turbine of claim 8, further comprising a plurality of flow grooves. 13. The turbine of claim 8, wherein the flow groove is shaped to reduce flow migration in a flow of hot combustion gases along the airfoil. 14. A turbine nozzle airfoil, comprising: an airfoil extending from a base to a tip, wherein the tip of the airfoil is inclined along a rotor axis, the airfoil comprising: a leading edge;a trailing edge,a pressure side;a suction side; anda flow groove extending from the leading edge to the trailing edge only along the suction side;wherein the flow groove extends inwardly from the suction side of the airfoil such that the flow groove has a depth measured from the suction side of the airfoil, the flow groove substantially parallel to the tip of the airfoil; andthe flow groove blends into the outer surface at the leading edge and the trailing edge of the airfoil, such that a first depth of the flow groove at either the leading edge or the trailing edge of the airfoil is less than a second depth of the flow groove along the suction side of the airfoil. 15. The turbine nozzle airfoil of claim 14, wherein the flow groove is positioned adjacent to the tip. 16. The turbine nozzle airfoil of claim 14, wherein the flow groove comprises a substantial V-like shape.