AIRFOIL SHAPE FOR TURBINE NOZZLES

• US 20200131911A1
• Filed: 10/31/2018
• Published: 04/30/2020
• Est. Priority Date: 10/31/2018
• Status: Active Grant

• Current Assignee: GE Infrastructure Technology, LLC (General Electric Company)
• Original Assignee: General Electric Company
• Inventors: Pierre, Sylvain, Zhang, Jinmei, Hall, Dustin James, Neeley, Marvin Luther
• Granted Patent: US 11,346,225 B2
• Time in Patent Office: Days
• 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: F01D 9/041 using blades F01D5/148 takes precedence
• CPC Class Codes: F05D 2220/3212 the first stage of a turbine
• CPC Class Codes: F05D 2240/123 related to the pressure side of a stator vane
• CPC Class Codes: F05D 2240/124 related to the suction side of a stator vane
• CPC Class Codes: F05D 2240/128 Nozzles
• CPC Class Codes: F05D 2250/74 given by a set or table of xyz-coordinates
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A turbine nozzle having an airfoil that includes a pressure side portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a pressure side as set forth in Table I. The Cartesian coordinate values of X, Y, and Z are non-dimensional values from 0% to 100% convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil defined along the Z axis. The X and Y values of the pressure side are coordinate values that, when connected by smooth continuing arcs, define pressure side sections of the pressure side portion of the nominal airfoil profile at each Z coordinate value. The pressure side sections may be joined smoothly with one another to form the pressure side portion.

Claims

1. A turbine nozzle including an airfoil that comprises a pressure side portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a pressure side as set forth in Table I, wherein:

the Cartesian coordinate values of X, Y, and Z are non-dimensional values from 0% to 100% convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil defined along a Z axis;

the X and Y values of the pressure side are coordinate values that, when connected by smooth continuing arcs, define pressure side sections of the pressure side portion of the nominal airfoil profile at each Z coordinate value; and

the pressure side sections are joined smoothly with one another to form the pressure side portion.

2. The turbine nozzle of claim 1, wherein the nominal airfoil profile lies in an envelope within +/−

5% of a chord length in a direction normal to any of the pressure side sections.

3. The turbine nozzle of claim 1, wherein a height of the pressure side portion is defined along the Z axis, and wherein the height of the pressure side portion is less than or equal to the height of the airfoil.

4. The turbine nozzle of claim 3, wherein the height of the pressure side portion is equal to or greater than 50% of the height of the airfoil;

and

wherein the height of the airfoil is between 3 and 10 inches.

5. The turbine nozzle of claim 3, wherein the height of the pressure side portion is equal to or greater than 75% of the height of the airfoil;

and

wherein the turbine nozzle is configured to function as a first stage turbine nozzle in a turbine.

6. The turbine nozzle of claim 3, wherein the height of the pressure side portion is equal to 100% of the height of the airfoil.

7. A turbine nozzle including an airfoil that comprises a suction side portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in Table I, wherein:

the Cartesian coordinate values of X, Y, and Z are non-dimensional values from 0% to 100% convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil defined along a Z axis;

the X and Y values of the suction side are coordinate values that, when connected by smooth continuing arcs, define suction side sections of the suction side portion of the nominal airfoil profile at each Z coordinate value; and

the suction side sections are joined smoothly with one another to form the suction side portion.

8. The turbine nozzle of claim 7, wherein the nominal airfoil profile lies in an envelope within +/−

5% of a chord length in a direction normal to any of the suction side sections.

9. The turbine nozzle of claim 7, wherein a height of the suction side portion is defined along the Z axis, and wherein the height of the suction side portion is less than or equal to the height of the airfoil.

10. The turbine nozzle of claim 9, wherein the height of the suction side portion is equal to or greater than 50% of the height of the airfoil;

and

wherein the height of the airfoil is between 3 and 10 inches.

11. The turbine nozzle of claim 9, wherein the height of the suction side portion is equal to or greater than 75% of the height of the airfoil;

and

wherein the turbine nozzle is configured to function as a first stage turbine nozzle in a turbine.

12. The turbine nozzle of claim 9, wherein the height of the suction side portion is equal to 100% of the height of the airfoil.

13. A turbine engine that includes an airfoil that comprises:

a pressure side portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a pressure side as set forth in Table I;

a suction side portion of the nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of the suction side as set forth in Table I;

wherein;

the Cartesian coordinate values of X, Y, and Z are non-dimensional values from 0% to 100% convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil defined along a Z axis;

the X and Y values of the pressure side are coordinate values that, when connected by smooth continuing arcs, define pressure side sections of the pressure side portion of the nominal airfoil profile at each Z coordinate value, the pressure side sections being joined smoothly with one another to form the pressure side portion; and

the X and Y values of the suction side are coordinate values that, when connected by smooth continuing arcs, define suction side sections of the suction side portion of the nominal airfoil profile at each Z coordinate value, the suction side sections being joined smoothly with one another to form the suction side portion.

14. The turbine engine of claim 13, wherein the turbine engine comprises a gas turbine having a compressor, a combustor, and a turbine;

and

wherein the airfoil is included within a nozzle in the turbine.

15. The turbine engine of claim 14, wherein the nozzle is a first stage nozzle in the turbine.

16. The turbine engine of claim 14, the nominal airfoil profile lies in an envelope within +/−

20% of a thickness of a trailing edge of the airfoil in a direction normal to any of the suction side and pressure side sections; and

wherein;

a height of the suction side portion is defined along the Z axis, and wherein the height of the suction side portion is less than or equal to the height of the airfoil; and

a height of the pressure side portion is defined along the Z axis, and wherein the height of the pressure side portion is less than or equal to the height of the airfoil.

17. The turbine engine of claim 16, wherein the height of the suction side portion and the height of the pressure side portion are substantially the same;

wherein the height of the suction side portion and the height of the pressure side portion are each equal to or greater than 50% of the height of the airfoil; and

wherein the suction side portion and the pressure side portion start at a common distance relative to a base of the airfoil and extend toward a tip of the airfoil.

18. The turbine engine of claim 17, wherein the height of the suction side portion and the height of the pressure side portion are each equal to or greater than 75% of the height of the airfoil.

19. The turbine engine of claim 17, wherein the height of the suction side portion and the height of the pressure side portion are each equal to or greater than 100% of the height of the airfoil.

20. The turbine engine of claim 17, wherein the turbine comprises a first stage that includes a row of first stage nozzles adjacent to a row of first stage rotor blades;

and

wherein a plurality of first stage nozzles contained within the row of first stage nozzles comprises the airfoil.