Airfoil shape for a turbine nozzle

• US 6,398,489 B1
• Filed: 02/08/2001
• Issued: 06/04/2002
• Est. Priority Date: 02/08/2001
• Status: Expired due to Fees

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Patik, Joseph Francis, Itzel, Gary Michael, Burdgick, Steven Sebastian
• Primary Examiner(s): Look, Edward K.
• Assistant Examiner(s): NGUYEN, NINH H
• Application Number:
  US09/779,226
• Time in Patent Office: 481 Days
• Field of Search: 415/191, 415/208.2, 415/115, 416/243, 416/DIG.2, 416/DIG.5
• US Class Current: 415/115
• CPC Class Codes: F01D 5/141 Shape, i.e. outer, aerodynamic form F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147

Abstract

A first-stage nozzle vane includes an airfoil having a profile according to Table I. The annulus profile of the hot gas path is defined in conjunction with the airfoil profile and the profile of the inner and outer walls by the Cartesian coordinate values given in Tables I and II, respectively. The airfoil is a three-dimensional bowed design, both in the airfoil body and in the trailing edge. The airfoil is steam and air-cooled by flowing cooling mediums through cavities extending in the vane between inner and outer walls.

Claims

1. An airfoil for a gas turbine nozzle stage having a profile at ambient temperature substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I as follows:

2. An airfoil according to claim 1 including a thermal barrier coating on said airfoil.

3. An airfoil according to claim 1 wherein said airfoil has a plurality of cavities within the airfoil extending substantially the entire length of the airfoil.

4. An airfoil according to claim 1 having an outer wall and an inner wall defining with said airfoil an airfoil segment.

5. An airfoil according to claim 4 wherein an inner diameter and an outer diameter of the inner outer walls, respectively, have profiles at ambient temperature substantially in accordance with Cartesian coordinate values of X, Y and Z as set forth in Table II as follows:

6. A nozzle stage for a gas turbine comprising:

forty-two airfoils spaced equally one from the other about a horizontal centerline of the gas turbine, each said airfoil having a profile at ambient temperature substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I as follows;

7. A nozzle stage according to claim 6 having outer and inner walls defining an annulus through the nozzle stage.

8. A nozzle stage according to claim 7 wherein the inner diameter and the outer diameter of the inner and outer walls, respectively, have profiles at ambient temperature substantially in accordance with Cartesian coordinate values of X, Y and Z as set forth in Table II as follows: