FILLET FOR USE WITH A TURBINE ROTOR BLADE TIP SHROUD

• US 20140154079A1
• Filed: 11/30/2012
• Published: 06/05/2014
• Est. Priority Date: 11/30/2012
• Status: Active Grant

• Current Assignee: GE Infrastructure Technology, LLC (GE Vernova, Inc.)
• Original Assignee: General Electric Company
• Inventors: Chouhan, Rohit, Bommanakatte, Harish, Soni, Sumeet, Jayana, Srinivasa Govardhan, Kareff, Spencer Aaron
• Granted Patent: US 9,322,282 B2
• Time in Patent Office: Days
• US Class Current: 416/179
• CPC Class Codes: F01D 5/143 Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
• CPC Class Codes: F01D 5/225 by shrouding
• CPC Class Codes: F05D 2240/307 related to the tip of a rotor blade
• CPC Class Codes: F05D 2250/74 given by a set or table of xyz-coordinates

Abstract

A turbine rotor blade is provided. The turbine rotor blade includes an airfoil, an airfoil tip, a tip shroud, and a fillet about an intersection of the airfoil tip and the tip shroud. The fillet defines a fillet profile variable about the intersection as a function of aerodynamic airflow about the intersection.

Claims

1. A turbine rotor blade comprising:

an airfoil having an airfoil tip;

a tip shroud; and

a fillet about an intersection of said airfoil tip and said tip shroud, said fillet defining a fillet profile variable about said intersection to facilitate improved aerodynamic airflow about said intersection.

2. A turbine rotor blade according to claim 1 wherein the fillet profile at a first point of intersection is one of a parabola, an ellipse and a hyperbola.

3. A turbine rotor blade according to claim 2 wherein the fillet profile at a second point of intersection is a curve different from said one parabola, an ellipse and hyperbola at said first point of intersection.

4. A turbine rotor blade according to claim 1, wherein said fillet defines a nominal profile substantially in accordance with coordinate values of X, Y, Z, offset 1, offset 2 and Rho set forth in Table I wherein X, Y, and Z define in inches discrete apex locations about the intersection of said airfoil tip and said tip shroud, offset 1 and offset 2 are respective distances in inches from each corresponding apex location to a fillet edge point defined between an undersurface of said tip shroud and an airfoil surface, wherein, upon connection about said respective tip shroud and said airfoil, said fillet edges are defined, and Rho is a non-dimensional shape parameter ratio of (D1/(D1+D2)) at each apex location, wherein D1 is a distance defined between a midpoint along a chord extending between said fillet edge points and a shoulder point defined on a surface of said fillet, and D2 is a distance defined between the shoulder point and said apex location, said fillet edge points on said tip shroud and said airfoil at each X, Y, and Z location being connected by a smooth continuing arc extending through said shoulder point in accordance with the shape parameter Rho to define a profile section at each said apex location, wherein said profile sections at each said apex location being joined smoothly with one another to form the nominal fillet profile.

5. A turbine rotor blade according to claim 4, wherein each said apex location defines one of points P1-P13 as set forth in Table I.

6. A turbine rotor blade according to claim 4, wherein said blade is coupled within a second stage of a turbine.

7. A turbine rotor blade according to claim 4, wherein said blade is coupled within a third stage of a turbine.

8. A turbine rotor blade according to claim 4, wherein the X, Y, and Z distances and the offsets 1 and 2 are scalable as a function of the same constant to provide one of a scaled up and a scaled down fillet profile.

9. A turbine rotor blade according to claim 4, wherein said fillet profile lies in an envelope defined within ±

0.050 inches in a direction normal to any fillet surface location.

10. A turbine rotor blade according to claim 4, wherein said X and Y values form a Cartesian coordinate system having a Z axis, said airfoil comprising an airfoil shape defining a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z as set forth in Table II, wherein the Z value is a non-dimensional value at 97.5% span of the airfoil and wherein X and Y values in Table II are distances in inches which, when connected by smooth continuing arcs, define an airfoil profile section at 97.5% span, the X, Y and Z Cartesian coordinate systems for the fillet and airfoil profile being coincident.

11. A turbine rotor blade according to claim 10, wherein the X and Y distances and the offsets 1 and 2 are scalable as a function of the same constant to provide one of a scaled up and a scaled down fillet profile.

12. A turbine rotor blade according to claim 10, wherein said airfoil profile lies in an envelope within ±

0.050 inches in a direction normal to any fillet surface location.

13. A gas turbine engine including a turbine rotor blade including an airfoil, an airfoil tip, a tip shroud, and a fillet about an intersection of said airfoil tip and said tip shroud, said fillet defining a fillet profile variable about said intersection as a function of aerodynamic airflow about said intersection.

14. A gas turbine engine according to claim 13, wherein said fillet defines a nominal profile substantially in accordance with coordinate values of X and Y, offset 1, offset 2 and Rho set forth in Table I wherein X and Y define in inches discrete apex locations about the intersection of the airfoil tip and tip shroud, offset 1 and offset 2 are distances in inches from each corresponding apex location to a fillet edge point along the tip shroud undersurface and airfoil surface, respectively, wherein, upon connection about the respective tip shroud and airfoil, the fillet edges are defined, and Rho is a non-dimensional shape parameter ratio of (D1/(D1+D2)) at each apex location, wherein D1 is a distance between a midpoint along a chord between said fillet edge points and a shoulder point on a surface of said fillet and D2 is a distance between the shoulder point and the apex location, said fillet edge points on said tip shroud and said airfoil at each X, Y location being connected by a smooth continuing arc passing through the shoulder point in accordance with the shape parameter Rho to define a profile section at each apex location, the profile sections at each apex location being joined smoothly with one another to form the nominal fillet profile.

15. A gas turbine engine according to claim 14, wherein each apex location defines one of points P1-P13 as set forth in Table I.

16. A gas turbine engine according to claim 14, wherein the X and Y distances and the offsets 1 and 2 are scalable as a function of the same constant or number to provide a scaled up or scaled down fillet profile.

17. A gas turbine engine according to claim 14, wherein said fillet profile lies in an envelope within ±

0.050 inches in a direction normal to any fillet surface location.

18. A gas turbine engine according to claim 14, wherein said X and Y values form a Cartesian coordinate system having a Z axis, said airfoil having an airfoil shape, the airfoil defining a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z as set forth in Table II wherein the Z value is a non-dimensional value at 97.5% span of the airfoil and wherein X and Y values in Table II are distances in inches which, when connected by smooth continuing arcs, define an airfoil profile section at 97.5% span, the X, Y and Z Cartesian coordinate systems for the fillet and airfoil profile being coincident.

19. A gas turbine engine according to claim 14, wherein the X and Y distances and the offsets 1 and 2 are scalable as a function of the same constant or number to provide a scaled up or scaled down fillet profile.

20. A gas turbine engine according to claim 14, wherein said airfoil profile lies in an envelope within ±

0.050 inches in a direction normal to any fillet surface location.