INTERNAL CORE PROFILE FOR A TURBINE NOZZLE AIRFOIL

• US 20050265829A1
• Filed: 05/26/2004
• Published: 12/01/2005
• Est. Priority Date: 05/26/2004
• Status: Active Grant

• Current Assignee: GE Infrastructure Technology, LLC (GE Vernova, Inc.)
• Original Assignee: General Electric Company
• Inventors: Humanchuk, David John, Coign, Robert W., Jacks, Curtis John
• Granted Patent: US 6,994,520 B2
• Time in Patent Office: Days
• US Class Current: 415/191
• CPC Class Codes: B22C 9/10 Cores; Manufacture or installation of cores breaker cores B22C9/084
• 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 5/18 Hollow blades, i.e. blades with cooling or heating channels or cavities structure of hollow blades in general F01D5/147; Heating, heat-insulating or cooling means on blades
• CPC Class Codes: F05D 2230/21 by casting
• CPC Class Codes: F05D 2230/211 by precision casting, e.g. microfusing or investment casting

Abstract

First stage nozzle airfoils have internal core profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein X, Y and Z values are in inches. The X and Y values are distances which, when connected by smooth continuing arcs, define internal core profile sections at each radial distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete internal core profile. The X, Y and Z distances may be scalable as a function of the same constant or number to provide a scaled-up or scaled-down internal core profile. The nominal internal core profile given by the X, Y and Z distances lies within an envelope of ±0.030 inches in directions normal to any internal core surface location.

Claims

1. A turbine nozzle segment including inner and outer platforms and an airfoil extending between said platforms, said airfoil having an internal nominal core profile at least a portion of which is substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I between Z value limits of 22.200 and 25.050, wherein said Z values between said limits are radial distances from a turbine axis to planes extending normal to the radii and wherein the X and Y values are distances in inches which, when connected by smooth continuing arcs, define internal core profile sections at each distance Z along the airfoil between said Z value limits, the profile sections at the Z distances between said limits being joined smoothly with one another to form said airfoil internal core profile.

2. A turbine nozzle segment according to claim 1 forming part of a first stage of a turbine.

3. A turbine nozzle segment according to claim 1 wherein said internal core profile lies in an envelope within ±

0.030 inches in a direction normal to any internal core surface location.

4. A turbine nozzle segment according to claim 1 wherein the X, Y and Z distances are scalable as a function of the same constant or number to provide a scaled-up or scaled-down internal core profile.

5. A turbine comprising a plurality of nozzle segments arranged in a circumferential array about an axis of the turbine, each said nozzle segment including inner and outer platforms and at least one airfoil extending between said platforms, each said airfoil having an internal nominal core profile at least a portion of which is substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I between Z value limits of 22.200 and 25.050, wherein said Z values between said limits are radial distances from a turbine axis to planes extending normal to the radii and wherein the X and Y values are distances in inches which, when connected by smooth continuing arcs, define internal core profile sections at each distance Z along the airfoil between said Z value limits, the profile sections at the Z distances between said limits being joined smoothly with one another to form said airfoil internal core profile.

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

7. A turbine according to claim 5 wherein said internal core profile lies in an envelope within ±

0.030 inches in a direction normal to any internal core surface location.

8. A turbine nozzle segment including inner and outer platforms and an airfoil extending between said platforms, said airfoil having an internal nominal core profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein the Z values are radial distances from a turbine axis to planes extending normal to the radii and wherein the X and Y values are distances in inches which, when connected by smooth continuing arcs, define internal core profile sections at each distance Z along the airfoil, the profile sections at the Z distances being joined smoothly with one another to form said airfoil internal core profile.

9. A turbine nozzle segment according to claim 8 forming part of a first stage of a turbine.

10. A turbine nozzle segment according to claim 8 wherein said internal core profile lies in an envelope within ±

0.030 inches in a direction normal to any internal core surface location.

11. A turbine comprising a plurality of nozzle segments in a circumferential array about an axis of the turbine, each said segment having inner and outer platforms and at least one airfoil extending between said platforms, each said airfoil having an internal nominal core profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein the Z values are radial distances from said turbine axis to planes extending normal to the radii, and wherein the X and Y values are distances in inches which, when connected by smooth continuing arcs, define internal core profile sections at each distance Z along the airfoil, the profile sections at the Z distances being joined smoothly with one another to form said airfoil internal core profile.

12. A turbine according to claim 11 forming part of a first stage of a turbine.

13. A turbine according to claim 11 wherein said internal core profile lies in an envelope within ±

0.030 inches in a direction normal to any internal core surface location.