TURBOMACHINE COMPONENT HAVING AN AIRFOIL CORE SHAPE

• US 20130039771A1
• Filed: 08/09/2011
• Published: 02/14/2013
• Est. Priority Date: 08/09/2011
• Status: Active Grant

• Current Assignee: GE Infrastructure Technology, LLC (GE Vernova, Inc.)
• Original Assignee: General Electric Company
• Inventors: Bielek, Craig Allen, Vedhagiri, Sivaraman, Check, Benjamin Michael, Pollard, Hal Feaster
• Granted Patent: US 8,814,511 B2
• Time in Patent Office: Days
• US Class Current: 416/223.A
• 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 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

A turbomachine component includes a turbine stator nozzle member having an airfoil core shape. The airfoil core shape includes a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in TABLE 1, 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 core shape.

Claims

1. A turbomachine component comprising:

a turbine stator nozzle member having an airfoil core shape, the airfoil core shape having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in TABLE 1, 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 core shape.

2. The turbomachine component according to claim 1, wherein the turbine stator nozzle member includes a first end that extends to a second end through an airfoil portion, the airfoil core shape defining the airfoil portion.

3. The turbomachine component according to claim 1, wherein the turbine stator nozzle member forms part of a nozzle assembly.

4. The turbomachine component according to claim 1, wherein turbine stator nozzle member comprises a third stage nozzle member.

5. The turbomachine component according to claim 1, wherein the nominal profile lies within an envelope within +0.100 inches and −

0.1000 inches in a direction normal to any of the airfoil profile sections.

6. A turbomachine comprising:

a turbine portion; and

a turbine stator nozzle member provided in the turbine portion, the turbine stator nozzle member having an airfoil core shape, the airfoil core shape having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in TABLE 1, 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 core shape.

7. The turbomachine according to claim 6, wherein the turbine stator nozzle member includes a first end that extends to a second end through an airfoil portion, the airfoil core shape defining the airfoil portion

8. The turbomachine according to claim 7, wherein the turbine stator nozzle member forms part of a nozzle assembly.

9. The turbomachine according to claim 8, wherein the turbine stator nozzle member comprises a third stage nozzle member.

10. The turbomachine according to claim 6, wherein the nominal profile lies within an envelope within +0.100 inches and −

0.100 inches in a direction normal to any of the airfoil profile sections.