First and second stage turbine airfoil shapes

• US 20060216144A1
• Filed: 03/28/2005
• Published: 09/28/2006
• Est. Priority Date: 03/28/2005
• Status: Abandoned Application

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Sullivan, Michael Adelbert, Ladoon, Dale W., Candela, Ferruccio, Fredmonski, Adam J.
• Application Number:
  US11/090,300
• Publication Number:
  US 20060216144A1
• 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: F01D 5/142 of the blades of successive rotor or stator blade-rows
• CPC Class Codes: F05D 2250/70 Shape
• CPC Class Codes: F05D 2250/74 given by a set or table of xyz-coordinates
• CPC Class Codes: Y10S 416/02 Formulas of curves

Abstract

The first stage nozzles and buckets have nominal airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and R set forth in Tables I and II, respectively, and second stage nozzles and buckets have nominal airfoil profiles substantially in accordance with Cartesian coordinate values set forth in Tables III and IV, respectively. The X, Y and R values are in millimeters. R represents distances along a radius from an axis of rotation of the turbine. For each airfoil, X and Y are distances which, when connected by smooth continuous arcs, define airfoil profile sections in planes normal to the radius at each distance R. The profile sections at the R distances for each airfoil are joined smoothly with one another to form the airfoil shape. The airfoil shapes given by the X, Y and R distances lie within envelopes of ±4.064 millimeters in a direction normal to any airfoil surface location therealong.

Claims

1. A turbine nozzle including an airfoil having an airfoil shape, said airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and R set forth in millimeters in Table I wherein R is a distance along a radius from an axis of rotation of the turbine and X and Y are distances which, when connected by smooth continuing arcs, define airfoil profile sections in planes normal to the radius and at each distance R, the profile sections at the R distances being joined smoothly with one another to form said airfoil 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 airfoil shape lies in an envelope within ±

4.064 millimeters in a direction normal to any airfoil surface location.

4. A turbine bucket including an airfoil having an airfoil shape, said airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and R set forth in millimeters in Table II wherein R is a distance along a radius from an axis of rotation of the turbine and X and Y are distances which, when connected by smooth continuing arcs, define airfoil profile sections in planes normal to the radius and at each distance R, the profile sections at the R distances being joined smoothly with one another to form said airfoil shape.

5. A turbine bucket according to claim 4 forming part of a first stage of a turbine.

6. A turbine bucket according to claim 4 wherein said airfoil shape lies in an envelope within 4.064 millimeters in a direction normal to any airfoil surface location.

7. A turbine nozzle including an airfoil having an airfoil shape, said airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and R set forth in millimeters in Table III wherein R is a distance along a radius from an axis of rotation of the turbine and X and Y are distances which, when connected by smooth continuous arcs, define airfoil profile sections in planes normal to the radius and at each distance R, the profile sections in planes normal to the radius and at the R distances being joined smoothly with one another to form said airfoil shape.

8. A turbine nozzle according to claim 7 forming part of a second stage of the turbine.

9. A turbine nozzle according to claim 7 wherein said airfoil shape lies in an envelope within ±

4.064 millimeters in a direction normal to any airfoil surface location.

10. A turbine bucket including an airfoil having an airfoil shape, said airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and R set forth in millimeters in Table IV wherein R is a distance along a radius from an axis of rotation of the turbine and X and Y are distances which, when connected by smooth continuous arcs, define airfoil profile sections in planes normal to the radius and at each distance R, the profile sections at the R distances being joined smoothly with one another to form the airfoil shape.

11. A turbine bucket according to claim 10 forming part of a second stage of the turbine.

12. A turbine bucket according to claim 10 wherein said airfoil shape lies in an envelope within ±

4.064 millimeters in a direction normal to any airfoil surface location.

13. A first stage of a turbine having a plurality of nozzles in a circumferential array thereof about a turbine axis and a plurality of buckets in a circumferential array thereof about said axis downstream of said nozzles, each said nozzle including an airfoil having an airfoil shape, said airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and R set forth in millimeters in Table I wherein R is a distance along a radius from the axis of rotation of the turbine and X and Y are distances which, when connected by smooth continuing arcs, define airfoil profile sections in planes normal to the radius and at each distance R, the profile sections at the R distances being joined smoothly with one another to form said airfoil shape, each said bucket including a bucket airfoil having an airfoil shape, said bucket airfoil having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and R set forth in millimeters Table II wherein R is a distance along a radius from the axis of rotation of the turbine and X and Y are distances which, when connected by smooth continuing arcs, define bucket airfoil profile sections in planes normal to the radius and at each distance R, the profile sections at the R distances of Table II being joined smoothly with one another to form said bucket airfoil shape.

14. A second turbine stage according to claim 13 wherein each said airfoil shape of each of said nozzle and said bucket lies in an envelope within ±

4.064 millimeters in a direction normal to any airfoil surface location therealong.

15. A second stage of a turbine having a plurality of nozzles in a circumferential array thereof about a turbine axis and a plurality of buckets in a circumferential array thereof about said axis downstream of said nozzles, each said nozzle including an airfoil having an airfoil shape, said airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and R set forth in millimeters in Table III wherein R is a distance along a radius from the axis of rotation of the turbine and X and y are distances which, when connected by smooth continuous arcs, define airfoil profile sections in planes normal to the radius and at each distance R, the profile sections at the R distances being joined smoothly with one another to form said airfoil shape, each said bucket including a bucket airfoil having an airfoil shape, said bucket airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and R set forth in millimeters in Table IV wherein R is a distance along a radius from the axis of rotation of the turbine and X and Y are distances which, when connected by smooth continuous arcs, define airfoil profile sections in planes normal to the radius and at each distance R, the profile sections at the R distances of Table IV being joined smoothly with one another to form said bucket airfoil shape

16. A second stage of a turbine according to claim 15 wherein each said airfoil shape of each of said nozzles and said buckets lie in an envelope within ±

4.064 millimeters in a direction normal to any airfoil surface location therealong.