Second-stage turbine nozzle airfoil

• US 6,503,054 B1
• Filed: 07/13/2001
• Issued: 01/07/2003
• Est. Priority Date: 07/13/2001
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Brunner, Frederick James, Vo, Thanh, Bielek, Craig Allen
• Primary Examiner(s): Look, Edward K.
• Assistant Examiner(s): Edgar, Richard A.
• Application Number:
  US09/903,853
• Publication Number:
  US 20030021680A1
• Time in Patent Office: 543 Days
• Field of Search: 415/115, 415/191, 415/208.2, 416/243, 416/DIG.2, 416/DIG.5
• 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 2240/301 Cross-sectional characteristics

Abstract

The second-stage nozzles have vanes comprising airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in inches in Table I with the X, Y and Z values commencing at the radially innermost aerodynamic section of the airfoil and then made relative to that section for the Z coordinate values. The X, Y and Z values may be scaled as a function of the same constant or number to provide a scaled-up or scaled-down airfoil section for the nozzle.

Claims

1. A turbine nozzle having a nozzle vane in the shape of an airfoil in an envelope within ±

0.100 inches in a direction normal to any airfoil surface location wherein the airfoil has an uncoated nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in inches in Table I with the X, Y and Z values commencing at a radially innermost aerodynamic section of the airfoil and then made relative to that section for the Z coordinate values, the profiles at the Z distances being joined smoothly with one another to form the complete airfoil shape.

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

3. A turbine nozzle having a nozzle vane in the shape of an airfoil having an uncoated nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in inches in Table I with the X, Y and Z values commencing at a radially innermost aerodynamic section of the airfoil and then made relative to that section for the Z coordinate values, the profiles at the Z distances being joined smoothly with one another to form the complete airfoil profile;

the X, Y and Z values being scaled as a function of the same constant or number to provide a scaled-up or scaled-down nozzle airfoil.

4. A turbine nozzle according to claim 3 forming part of a second stage of a turbine.

5. A turbine comprising a turbine nozzle having a plurality of vanes, each of said vanes being in the shape of an airfoil in an envelope within ±

0.100 inches in a direction normal to any nozzle airfoil surface location wherein the airfoil has an uncoated nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in inches in Table I with the X, Y and Z values commencing at a radially innermost aerodynamic section of the airfoil and then made relative to that section for the Z coordinate values, the profiles at the Z distances being joined smoothly with one another to form the complete airfoil shape.

6. A turbine according to claim 5 wherein the turbine nozzle comprises a second stage of the turbine.

7. A turbine according to claim 5 wherein the turbine nozzle has sixty vanes.

8. A turbine comprising a turbine nozzle having a plurality of vanes, each of said vanes being in the shape of an airfoil having an uncoated nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in inches in Table I with the X, Y and Z values commencing at the radially innermost aerodynamic section of the airfoil and then made relative to that section for the Z coordinate values, the profiles at the Z distances being joined smoothly with one another to form the complete airfoil shape;

the X, Y and Z values being scaled as a function of the same constant or number to provide a scaled-up or scaled-down nozzle airfoil.

9. A turbine according to claim 8 wherein the turbine nozzle comprises a second stage of the turbine.

10. A turbine according to claim 8 wherein the turbine nozzle has sixty vanes.