TURBINE BLADE AIRFOIL AND TIP SHROUD

• US 20160115795A1
• Filed: 05/20/2014
• Published: 04/28/2016
• Est. Priority Date: 05/21/2013
• Status: Active Grant

• Current Assignee: Siemens Energy Incorporated (Siemens AG)
• Original Assignee: Siemens Energy Incorporated (Siemens AG)
• Inventors: Munoz, Eric, Kite, Edwin Lee, Pula, John, Evans, Charles M.
• Granted Patent: US 9,828,858 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• 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: F05D 2240/301 Cross-sectional characteristics
• CPC Class Codes: F05D 2250/74 given by a set or table of xyz-coordinates

Abstract

A turbine blade airfoil (25, 31R, 31M, 31T, 72) comprising an outer surface shape defined by Cartesian coordinates of successive transverse profiles at radial increments as set forth in Tables 1a to 1k, wherein each table defines a transverse sectional profile characterized by a smooth curve connecting the coordinates, and the surface shape comprises a smooth surface connecting the sectional profiles. The blade may include a tip shroud with edge profiles defined by Cartesian coordinates set forth in Table 2a and 2b. A gusset/fillet may be provided between the blade airfoil and the tip shroud, with a planar diagonal surface over most of a diagonal bracing area of the gusset/fillet.

Claims

1. A turbine blade airfoil comprising an outer surface shape defined by Cartesian coordinate values of X and Y at successive radial increments as set forth in Tables 1a to 1k, wherein each said table defines a transverse sectional profile characterized by a smooth curve connecting the X and Y coordinates, and the surface shape comprises a smooth surface connecting the sectional profiles.

2. The turbine blade airfoil of claim 1, wherein the Cartesian coordinate values are absolute values in inches, and a manufacturing tolerance of the smooth surface is +/−

0.050 inches measured normal to said surface.

3. The turbine blade airfoil of claim 1, wherein the Cartesian coordinate values are relative values, and a manufacturing tolerance of the smooth surface is a relative value of +/−

0.050 inches measured normal to said surface.

4. The turbine blade airfoil of claim 1, further comprising a tip shroud comprising an axially forward edge profile defined by Cartesian coordinate values of X and Y set forth in Table 2a, and an axially aft edge profile defined by Cartesian coordinate values of X and Y set forth in table 2b.

5. The turbine blade airfoil of claim 4, wherein the Cartesian coordinate values are absolute values in inches, and a manufacturing tolerance of the axially forward and aft profiles is +/−

0.050 inches measured normal to said profiles.

6. The turbine blade airfoil of claim 4, wherein the Cartesian coordinate values are relative values, and a manufacturing tolerance of the axially forward and aft profiles is a relative value of +/−

0.050 inches measured normal to said profiles.

7. The turbine blade airfoil of claim 1, further comprising a tip shroud on a tip of the blade airfoil, and a gusset/fillet between the blade airfoil the tip shroud, the gusset/fillet comprising a planar diagonal surface over most of a diagonal bracing area thereof, and two planar side facets, wherein the diagonal surface and side facets merge with the blade airfoil via a continuous fillet.