Stator blade airfoil profile for a compressor

• US 7,467,926 B2
• Filed: 06/09/2006
• Issued: 12/23/2008
• Est. Priority Date: 06/09/2006
• Status: Active Grant

• Current Assignee: GE Infrastructure Technology, LLC (General Electric Company)
• Original Assignee: General Electric Company
• Inventors: Stampfli, John David, Cummins, Josef Scott
• Primary Examiner(s): Look; Edward
• Assistant Examiner(s): WIEHE, NATHANIEL EDWARD
• Application Number:
  US11/449,770
• Publication Number:
  US 20070286718A1
• Time in Patent Office: 928 Days
• Field of Search: 416/223.A, 416/223.R, 416/243, 416/DIG.2
• US Class Current: 416/223.00A
• CPC Class Codes: F04D 29/544 Blade shapes
• CPC Class Codes: Y10S 416/02 Formulas of curves

Abstract

Tenth stage stator vanes for a compressor comprise airfoil profiles substantially in accordance with Cartesian coordinate values of x, Y and Z set forth in inches in Table I, wherein the Z coordinate values are perpendicular distances from planes normal to a radius from the compressor centerline and containing the X and Y values with the Z value commencing at zero in the X, Y plane at a radial aerodynamic section of the airfoil. X and Y are coordinate values defining the airfoil profile at each distance Z. The X, Y and Z values may be scaled to provide a scaled-up or scaled-down airfoil section for each stator vane.

Claims

1. A stator blade for a compressor having an airfoil, the airfoil having a shape 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 wherein the Z coordinate values are perpendicular distances from planes normal to a radius from the compressor centerline and containing the X and Y values with the Z value commencing at zero in the X, Y plane at a radial aerodynamic section of the airfoil and X and Y are coordinate values which, when connected by smooth continuing arcs, define the airfoil profile at each distance Z, the profiles at the Z distances being joined smoothly with one another to form the complete airfoil shape.

2. A stator blade according to claim 1, forming part of a tenth stage of a compressor.

3. A blade according to claim 1, wherein the Z=0 value commences at a radial distance of 17.322 inches from the compressor centerline and the Z values are increasingly positive in Table I in a radially outward direction.

4. A stator blade for a compressor having an airfoil, the 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, wherein the Z coordinate values are perpendicular distances from planes normal to a radius from the compressor centerline and containing the X and Y values with the Z values commencing at zero in the X, Y plane at a radial aerodynamic section of the airfoil and X and Y are coordinate values which, when connected by smooth continuing arcs, define the airfoil profile at each distance Z, 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 compressor airfoil.

5. A stator blade according to claim 4, forming part of the tenth stage of the compressor.

6. A blade according to claim 4, wherein the Z=0 value commences at a radial distance of 17.322 inches from the compressor centerline and the Z values are increasingly positive in a radially outward direction.

7. A compressor comprising a plurality of stator blades forming a portion of a compressor stage, each of said blades being in the shape of an airfoil 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, wherein the Z coordinate values are perpendicular distances from planes normal to a radius from the compressor centerline and containing the X and Y values with the Z values commencing at zero in the X, Y plane at a radial aerodynamic section of the airfoil and X and Y are coordinate values which, when connected by smooth continuing arcs, define the airfoil profile at each distance Z, the profiles at the Z distances being joined smoothly with one another to form the complete airfoil shape.

8. A compressor according to claim 7, wherein the compressor stage is the tenth stage.

9. A compressor according to claim 7, wherein the Z=0 value commences at a radial distance of 17.322 inches from the compressor centerline and the Z values are increasingly positive in a radially outward direction.

10. A compressor comprising a plurality of stator blades forming a portion of a compressor stage, each of said blades being in the shape of an airfoil 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, wherein the Z coordinate values are perpendicular distances from planes normal to a radius from the compressor centerline and containing the X and Y values with the Z values commencing at zero in the X, Y plane at a radial aerodynamic section of the airfoil and X and Y are coordinate values which, when connected by smooth continuing arcs, define the airfoil profile at each distance Z, the profiles at the Z distances being joined smoothly with one another to form the complete airfoil shape.

11. A compressor according to claim 10, wherein the compressor stage is the tenth stage.

12. A compressor according to claim 10, wherein the Z=0 value commences at a radial distance of 17.322 inches from the compressor centerline and the Z values are increasingly positive in a radially outward direction.