Turbine vane nominal airfoil profile

• US 8,585,360 B2
• Filed: 09/09/2010
• Issued: 11/19/2013
• Est. Priority Date: 09/09/2010
• Status: Active Grant

• Current Assignee: Siemens Energy Incorporated (Siemens AG)
• Original Assignee: Siemens Energy Incorporated (Siemens AG)
• Inventors: Islam, Alamgir T., Eshak, Daniel M., Gear, Paul J.
• Primary Examiner(s): Look, Edward
• Assistant Examiner(s): EASTMAN, AARON ROBERT
• Application Number:
  US12/878,210
• Publication Number:
  US 20120063908A1
• Time in Patent Office: 1,167 Days
• Field of Search: 415/191, 416/223.A, 416/223.R, 416/243, 416/DIG.2
• 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 9/041 using blades F01D5/148 takes precedence
• CPC Class Codes: F05D 2250/74 given by a set or table of xyz-coordinates

Abstract

A turbine vane for a turbine machine comprising an intermediate section having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein Z is a radial distance along a stacking axis that is normal to a centerline of the turbine machine and contain the X and Y values with Z value beginning at innermost aerodynamic point and the Z values represent a radial height of the vane and the X and Y values define the nominal airfoil profile at each radial height Z.

Claims

1. A turbine vane for a turbine machine comprising an intermediate section having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein Z is a radial distance along a stacking axis that is normal to a centerline of the turbine machine and contain the X and Y values with Z value beginning at innermost aerodynamic point and the Z values represent a radial height of the vane and the X and Y values define the nominal airfoil profile at each radial height Z.

2. The turbine vane of claim 1 wherein the vane is a stationary component of a turbine stage for the turbine machine.

3. The turbine vane of claim 2 wherein the vane is a stationary component of a second turbine stage for the turbine machine.

4. The turbine vane of claim 1 wherein the X and Y values are linearly or geometrically scalable up or down as a function of the same constant or number.

5. The turbine vane of claim 1 wherein the X and Y values have a nominal profile tolerance of ±

2.5 millimeters.

6. The turbine vane of claim 5 wherein the nominal airfoil profile is for an uncoated intermediate section of the turbine vane.

7. The turbine vane of claim 1 wherein the X and Y values define a set of points for each Z value which when connected by smooth continuing arcs define an airfoil profile of the intermediate section of the vane, and the profile sections at the Z heights being joined smoothly with one another to form an airfoil shape of the intermediate portion.

8. A stationary turbine vane for a turbine machine comprising a contoured uncoated intermediate section for controlling gas flow through a turbine vane block on which the stationary vane is mounted and the intermediate section having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein Z is a radial distance along a stacking axis that is normal to a centerline of the turbine machine and contain the X and Y values with Z value beginning at zero at an innermost aerodynamic point and the Z values represent a radial height of the vane and the X and Y values define the nominal airfoil profile at each radial height Z, and the X and Y values have a nominal profile tolerance of ±

2.5 millimeters.

9. The stationary turbine vane of claim 8 wherein the X and Y values are linearly or geometrically scalable up or down as a function of the same constant or number.

10. The stationary turbine vane of claim 9 wherein the intermediate section has a leading edge disposed toward a gas flow ingress to the turbine block, a trailing edge disposed toward a gas flow egress to the turbine block, a pressure side disposed between the leading edge and trail edge and a suction side opposite the pressure side.

11. The stationary turbine vane of claim 8 wherein the X and Y values define a set of points for each Z value which when connected by smooth continuing arcs define an airfoil profile of the intermediate section of the vane, and the profile sections at the Z heights being joined smoothly with one another to form an airfoil shape of the intermediate portion.

12. The stationary turbine vane of claim 8 wherein the turbine vane block is a component of a second stage of a turbine machine.

13. A turbine machine comprising at least one stage including a turbine vane block positioned upstream a gas flow relative to a turbine blade block, wherein the turbine vane block includes a plurality of stationary vanes circumferentially spaced about a rotating shaft of the turbine machine to control gas flow from a compressor and combustor to the turbine blade block, and each stationary vane comprises an intermediate having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein Z is a radial height along a stacking axis that is normal to a centerline of the turbine machine and contain the X and Y values with Z value beginning at zero at an innermost aerodynamic point and the Z values represent a radial height of the vane and the X and Y values define the nominal airfoil profile at each radial height Z.

14. The turbine machine of claim 13 wherein the turbine includes multiple stages and the turbine vanes are a component of a second stage of the turbine machine.

15. The turbine machine of claim 13 wherein the X and Y values of the nominal airfoil profile are linearly or geometrically scalable up or down as a function of the same constant or number.

16. The turbine machine of claim 13 wherein the X and Y values of the nominal airfoil profile have a nominal profile tolerance of ±

2.5 millimeters.

17. The turbine machine of claim 16 wherein the nominal airfoil profile is for an uncoated intermediate section of the turbine vane.

18. The turbine machine of claim 13 wherein the X and Y values define a set of points for each Z value which when connected by smooth continuing arcs define an airfoil profile of the intermediate section of the vane, and the profile sections at the Z heights being joined smoothly with one another to form an airfoil shape of the intermediate portion.