Airfoil shape for a turbine nozzle

• US 20080101925A1
• Filed: 10/26/2006
• Published: 05/01/2008
• Est. Priority Date: 10/26/2006
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Farral, Linda, Bielek, Craig, MacMillan, Glen, Humanchuk, Craig
• Granted Patent: US 7,527,473 B2
• Time in Patent Office: Days
• US Class Current: 415/208.1
• CPC Class Codes: F01D 9/041 using blades F01D5/148 takes precedence
• CPC Class Codes: F05D 2250/74 given by a set or table of xyz-coordinates

Abstract

The first stage nozzles have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth Table I. The X and Y values are in inches and the Z value is in inches along the nozzle stacking axis coincident with a turbine radius. The X and Y distances may be scalable as a function of the same constant or number to provide a scaled up or scaled down airfoil section for the nozzle. The nominal airfoil given by the X, Y and Z distances lies within an envelope of ±0.160 inches.

Claims

1. A turbine nozzle having an airfoil shape in an envelope within ±

0.160 inches in a direction normal to any airfoil surface location wherein the airfoil has a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I, X and Y being distances in inches defining the airfoil profile at each distance Z, the profiles at the Z distances being joined smoothly with one another to form a complete airfoil shape.

2. The turbine nozzle according to claim 1, wherein the turbine nozzle comprises a first stage nozzle of a turbine.

3. The turbine nozzle according to claim 1, wherein the Z value is measured from an intersection of a centerline of the nozzle along a radius from an axis of the turbine and a root radius of a flow path through the turbine.

4. A turbine nozzle having an uncoated nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I, Z being a non-dimensional value along a nozzle stacking axis coincident with a radius from a turbine axis of rotation and a Z distance in inches from said turbine axis, X and Y are distances in inches defining the airfoil profile at each distance Z, the profiles at the Z distances being joined smoothly with one another to form a complete airfoil shape.

5. The turbine nozzle according to claim 4, wherein X and Y are distances being scalable as a function of the same constant or number to provide a scaled-up or scaled-down nozzle airfoil.

6. The turbine nozzle according to claim 5 comprising a first stage nozzle of a turbine.

7. The turbine nozzle according to claim 4, wherein Z is a distance being scalable as a function of the same constant or number to provide a scaled-up or scaled-down nozzle airfoil.

8. A turbine comprising a nozzle arrangement having a plurality of nozzles, each nozzle including an airfoil having an uncoated nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table I, wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches, the profile sections at the Z distance being joined smoothly with one another to form a complete airfoil shape.

9. The turbine according to claim 8, wherein said airfoil shape lies in an envelope within ±

0.160 inches in a direction normal to any airfoil surface location.

10. The turbine according to claim 9, wherein the nozzle arrangement comprises a first stage nozzle of the turbine.

11. The turbine according to claim 10, wherein the first stage nozzle comprises 48 nozzles and Y represents a distance parallel to an axis of rotation of the turbine.

12. The turbine according to claim 8, wherein the nominal profile for said airfoil comprises an uncoated nominal profile, said X and Y distances being scalable as a function of the same constant or number.

13. The turbine according to claim 12, wherein the nozzle arrangement comprises a first stage nozzle of the turbine.

14. The turbine according to claim 13, wherein the first stage nozzle comprises 48 nozzles and Y represents a distance parallel to an axis of rotation of the turbine.

15. The turbine according to claim 8, wherein said Z distance being scalable as a function of the same constant or number.