AIRFOIL SHAPE AND SIDEWALL FLOWPATH SURFACES FOR A TURBINE NOZZLE

• US 20060024159A1
• Filed: 07/28/2004
• Published: 02/02/2006
• Est. Priority Date: 07/28/2004
• Status: Active Grant

• Current Assignee: GE Infrastructure Technology, LLC (General Electric Company), Ipsen Manufacturing Ireland Limited (Henri Beaufour)
• Original Assignee: General Electric Company
• Inventors: Phillips, James Stewart, Gill, Randall Douglas, Wedlake, Raymond Allan
• Granted Patent: US 7,001,147 B1
• Time in Patent Office: Days
• US Class Current: 415/191
• CPC Class Codes: F01D 5/141 Shape, i.e. outer, aerodynamic form F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147
• CPC Class Codes: F05D 2250/70 Shape
• CPC Class Codes: F05D 2250/74 given by a set or table of xyz-coordinates

Abstract

A turbine nozzle includes airfoil and sidewall surfaces. The airfoil and sidewall surfaces have profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Tables I-IV for the pressure and suction sides of the airfoil, and the outer and inner sidewall surfaces, respectively. The X, Y and Z values are distances in inches. The X and Y values for the airfoil, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The profile sections at the Z distances are joined smoothly with one another to form a complete airfoil shape. The X, Y and Z values of Tables III and IV define the outer and inner sidewall surfaces, respectively, of the gas flowpath.

Claims

1. A turbine nozzle having a pressure side airfoil surface, said pressure side airfoil surface having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in inches in Table I, wherein the Z values are drop dimensions from a reference point origin on an outside diameter flowpath along a nozzle airfoil stacking axis perpendicular to a centerline axis of rotation of the turbine;

and wherein the X and Y values, when connected by smooth continuing arcs, define pressure side airfoil surface profile sections at each distance Z from said origin, the profile sections at the Z distances being joined smoothly with one another to form a pressure side airfoil surface shape.

2. A turbine nozzle according to claim 1, forming part of a first stage of a turbine.

3. A turbine nozzle according to claim 1, wherein said pressure side airfoil surface lies in an envelope within ±

0.105 inches in a direction normal to any pressure side airfoil surface location.

4. A turbine nozzle according to claim 3, wherein said pressure side airfoil surface is coated, the X, Y and Z distances being scalable as a function of the same constant or number to provide a scaled up or scaled down pressure side airfoil surface shape.

5. A turbine nozzle according to claim 1, having an outer sidewall surface, said outer sidewall surface having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in inches in Table III, wherein the Z values are drop dimensions from said reference point origin on an outside diameter flowpath along a nozzle airfoil stacking axis perpendicular to a centerline axis of rotation of the turbine;

and wherein the X and Y values, when connected by smooth continuing arcs at each distance Z, define an outer sidewall surface shape.

6. A turbine nozzle according to claim 1, having an inner sidewall surface, said inner sidewall surface having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in inches in Table IV, wherein the Z values are drop dimensions from said reference point origin on an outside diameter flowpath along a nozzle airfoil stacking axis perpendicular to a centerline axis of rotation of the turbine;

and wherein the X and Y values, when connected by smooth continuing arcs at each distance Z, define an inner sidewall surface shape.

7. A turbine nozzle according to claim 1, having a suction side airfoil, said suction side airfoil surface having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in inches in Table II, wherein the Z values are drop dimensions from said reference point origin on an outside diameter flowpath along a nozzle airfoil stacking axis perpendicular to a centerline axis of rotation of the turbine;

and wherein the X and Y values, when connected by smooth continuing arcs, define suction side airfoil surface profile sections at each distance Z from said origin, the profile sections at the Z distances being joined smoothly with one another to form a suction side airfoil surface shape.

8. A turbine nozzle having a suction side airfoil surface, said suction side airfoil surface having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in inches in Table II, wherein the Z values are drop dimensions from a reference point origin on an outside diameter flowpath along a nozzle airfoil stacking axis perpendicular to a centerline axis of rotation of the turbine;

and wherein the X and Y values, when connected by smooth continuing arcs, define suction side airfoil surface profile sections at each distance Z from said origin, the profile sections at the Z distances being joined smoothly with one another to form a suction side airfoil surface shape.

9. A turbine nozzle according to claim 8, forming part of a first stage of a turbine.

10. A turbine nozzle according to claim 8, wherein said suction side airfoil surface lies in an envelope within ±

0.105 inches in a direction normal to any suction side airfoil surface location.

11. A turbine nozzle according to claim 10, wherein said suction side airfoil surface is coated, the X, Y and Z distances being scalable as a function of the same constant or number to provide a scaled up or scaled down suction side airfoil surface shape.

12. A turbine nozzle according to claim 8, having an outer sidewall surface, said outer sidewall surface having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in inches in Table III, wherein the Z values are drop dimensions from said reference point origin on an outside diameter flowpath along a nozzle airfoil stacking axis perpendicular to a centerline axis of rotation of the turbine;

and wherein the X and Y values, when connected by smooth continuing arcs at each distance Z, define an outer sidewall surface shape.

13. A turbine nozzle according to claim 8, having an inner sidewall surface, said inner sidewall surface having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in inches in Table IV, wherein the Z values are drop dimensions from said reference point origin on an outside diameter flowpath along a nozzle airfoil stacking axis perpendicular to a centerline axis of rotation of the turbine;

and wherein the X and Y values, when connected by smooth continuing arcs at each distance Z, define an inner sidewall surface shape.

14. A turbine nozzle having an outer sidewall surface, said outer sidewall surface having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in inches in Table III, wherein the Z values are drop dimensions from a reference point origin on an outside diameter flowpath along a nozzle airfoil stacking axis perpendicular to a centerline axis of rotation of the turbine;

and wherein the X and Y values, when connected by, smooth continuing arcs at each distance Z, define an outer sidewall surface shape.

15. A turbine nozzle according to claim 14, forming part of a first stage of a turbine.

16. A turbine nozzle according to claim 14, wherein said outer sidewall surface lies in an envelope within ±

0.105 inches in a direction normal to any outer sidewall surface location.

17. A turbine nozzle according to claim 16, wherein said outer sidewall surface is coated, the X, Y and Z distances being scalable as a function of the same constant or number to provide a scaled up or scaled down outer sidewall surface shape.

18. The turbine nozzle of claim 14 having an inner sidewall, said inner sidewall surface having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in inches in Table IV, wherein the Z values are drop dimensions from said reference point origin on an outside diameter flowpath along a nozzle airfoil stacking axis perpendicular to a centerline axis of rotation of the turbine;

and wherein the X and Y values, when connected by smooth continuing arcs at each distance Z, define an inner sidewall surface shape.

19. A turbine nozzle having an inner sidewall surface, said inner sidewall surface having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in inches in Table IV, wherein the Z values are drop dimensions from a reference point origin on an outside diameter flowpath along a nozzle airfoil stacking axis perpendicular to a centerline axis of rotation of the turbine;

and wherein the X and Y values, when connected by smooth continuing arcs at each distance Z, define an inner sidewall surface shape.

20. A turbine nozzle according to claim 19, forming part of a first stage of a turbine.

21. A turbine nozzle according to claim 19, wherein said inner sidewall surface lies in an envelope within ±

0.105 inches in a direction normal to any inner sidewall surface location.

22. A turbine nozzle according to claim 21, wherein said inner sidewall surface is coated, the X, Y and Z distances being scalable as a function of the same constant or number to provide a scaled up or scaled down inner sidewall surface shape.

23. A turbine comprising a turbine nozzle having a plurality of airfoils having an airfoil shape, each said airfoil having pressure and suction side airfoil surfaces defining a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Tables I and II, wherein the Z values are drop dimensions from a reference point origin on an outside diameter flowpath along a nozzle airfoil stacking axis perpendicular to a centerline axis of rotation of the turbine, and wherein the X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the profile sections at the Z distances being joined smoothly with one another to form an airfoil shape.

24. The turbine according to claim 23 including an inner sidewall, said inner sidewall surface having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in inches in Table IV, wherein the Z values are drop dimensions from said reference point origin on an outside diameter flowpath along a nozzle airfoil stacking axis perpendicular to a centerline axis of rotation of the turbine;

and wherein the X and Y values, when connected by smooth continuing arcs at each distance Z, define an inner sidewall surface shape.

25. The turbine according to claim 23, including an outer sidewall, said outer sidewall surface having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in inches in Table III, wherein the Z values are drop dimensions from said reference point origin on an outside diameter flowpath along a nozzle airfoil stacking axis perpendicular to a centerline axis of rotation of the turbine;

and wherein the X and Y values, when connected by smooth continuing arcs at each distance Z, define an outer sidewall surface shape.

26. The turbine according to claim 25, including an inner sidewall, said inner sidewall surface having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in inches in Table IV, wherein the Z values are drop dimensions from said reference point origin on an outside diameter flowpath along a nozzle airfoil stacking axis perpendicular to a centerline axis of rotation of the turbine;

and wherein the X and Y values, when connected by smooth continuing arcs at each distance Z, define an inner sidewall surface shape.