AIRFOIL SHAPE FOR A TURBINE NOZZLE

• US 20100158678A1
• Filed: 12/22/2008
• Published: 06/24/2010
• Est. Priority Date: 12/22/2008
• Status: Active Grant

• Current Assignee: GE Infrastructure Technology, LLC (General Electric Company)
• Original Assignee: General Electric Company
• Inventors: Bielek, Craig A., Blow, Gerald K., Brock, Donald O.
• Granted Patent: US 8,070,428 B2
• Time in Patent Office: Days
• US Class Current: 415/193
• CPC Class Codes: F01D 5/142 of the blades of successive rotor or stator blade-rows
• CPC Class Codes: F01D 9/041 using blades F01D5/148 takes precedence
• CPC Class Codes: F05D 2240/12 Fluid guiding means, e.g. vanes
• CPC Class Codes: F05D 2250/74 given by a set or table of xyz-coordinates

Abstract

An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a table. Wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches, the profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape.

Claims

1. An article of manufacture, the article having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a table, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches, the profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape.

2. An article of manufacture according to claim 1, wherein the article comprises an airfoil.

3. An article of manufacture according to claim 2, wherein said article shape lies in an envelope within ±

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

4. An article of manufacture according to claim 1, wherein the article comprises a turbine nozzle.

5. An article of manufacture according to claim 5, wherein the turbine nozzle comprises a third stage turbine nozzle.

6. A turbine comprising at least one turbine nozzle, each said turbine nozzle including an airfoil having an airfoil shape, said airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a table, wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define the airfoil profile sections at each distance Z in inches, the profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape.

7. A turbine nozzle according to claim 6 wherein the compressor wheel rotor blades.

8. A turbine comprising at least one turbine nozzle, each said turbine nozzle including an airfoil having an uncoated nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a table, wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches, the profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape, the X and Y distances being scalable as a function of the same constant or number to provide a scaled-up or scaled-down rotor blade airfoil.

9. A turbine according to claim 8 wherein the turbine comprises a third stage of a turbine nozzle.

10. A compressor according to claim 8 wherein the compressor wheel has 66 rotor blades.

11. A compressor according to claim 8 wherein said airfoil shape lies in an envelope within ±

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