Stator blade airfoil profile for a compressor

• US 7,396,211 B2
• Filed: 03/30/2006
• Issued: 07/08/2008
• Est. Priority Date: 03/30/2006
• Status: Expired due to Fees

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Tomberg, Steven Eric, Chaluvadi, Venkata Siva
• Primary Examiner(s): Kershteyn; Igor
• Application Number:
  US11/392,514
• Publication Number:
  US 20070231147A1
• Time in Patent Office: 831 Days
• Field of Search: 415/191, 415/192, 415/208.1, 415/208.2, 416/223.A, 416/223.R, 416/243, 416/241.R, 416/DIG.2, 416/DIG.5
• US Class Current: 416/223.00A
• 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: F04D 29/544 Blade shapes
• CPC Class Codes: Y10S 416/02 Formulas of curves
• CPC Class Codes: Y10S 416/05 Variable camber or chord length

Abstract

Eleventh 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 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 an eleventh stage of a compressor.

3. A stator blade according to claim 1, wherein the airfoil has a shape in an envelope within ±

0.100 inches in a direction normal to any airfoil surface location.

4. A stator blade according to claim 1, wherein the Z=0 value commences at a radial distance of about 17.205 inches from the compressor centerline and the Z values are increasingly positive in Table I in a radially outward direction.

5. 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.

6. A stator blade according to claim 5, forming part of an eleventh stage of the compressor.

7. A stator blade according to claim 5, wherein the airfoil has a shape in an envelope within ±

0.100 inches in a direction normal to any airfoil surface location.

8. A stator blade according to claim 5, wherein the Z=0 value commences at a radial distance of about 17.205 inches from the compressor centerline and the Z values are increasingly positive in a radially outward direction.

9. 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 having 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.

10. A compressor according to claim 9, wherein the compressor stage is the eleventh stage.

11. A compressor according to claim 9, wherein the airfoil has a shape in an envelope within ±

0.100 inches in a direction normal to any airfoil surface location.

12. A compressor according to claim 9, wherein the Z=0 value commences at a radial distance of about 17.205 inches from the compressor centerline and the Z values are increasingly positive in a radially outward direction.

13. A compressor according to claim 9, wherein the X, Y and Z values are scaled as a function of the same constant or number to provide a scaled-up or scaled-down compressor airfoil.