Cooled turbine blade

• US 7,632,071 B2
• Filed: 12/15/2005
• Issued: 12/15/2009
• Est. Priority Date: 12/15/2005
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: Palmer, Steve, Pietraskiewicz, Edward F., Charbonneau, Robert, Downs, James, Widmer, Wanda, Gregg, Shawn, Khandros, Natalya, Roeloffs, Norm, Stockton, Richard, Williams, Dagny, Orndoff, Paul, Harris, Wesley, Levine, Jeffrey R.
• Primary Examiner(s): EDGAR, RICHARD A
• Application Number:
  US11/303,593
• Publication Number:
  US 20070140848A1
• Time in Patent Office: 1,461 Days
• Field of Search: 416/92
• US Class Current: 416/92
• CPC Class Codes: F01D 5/081 Cooling fluid being directed on the side of the rotor disc or at the roots of the blades F01D5/087 takes precedence
• 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 5/145 Means for influencing boundary layers or secondary circulations for compressors F04D29/68
• CPC Class Codes: F01D 5/187 Convection cooling
• CPC Class Codes: F01D 5/20 Specially-shaped blade tips to seal space between tips and stator F01D5/225 takes precedence
• CPC Class Codes: F05D 2240/122 related to the trailing edge of a stator vane
• CPC Class Codes: F05D 2240/304 related to the trailing edge of a rotor blade
• CPC Class Codes: F05D 2240/80 Platforms for stationary or moving blades
• CPC Class Codes: F05D 2250/185 serpentine-like
• CPC Class Codes: F05D 2250/232 conical
• CPC Class Codes: F05D 2250/314 the axes being inclined in relation to each other
• CPC Class Codes: F05D 2250/712 concave
• CPC Class Codes: F05D 2260/607 Preventing clogging or obstruction of flow paths by dirt, dust, or foreign particles

Abstract

A turbine engine component, such as a turbine blade, has an airfoil portion, a plurality of cooling passages within the airfoil portion with each of the cooling passages having an inlet for a cooling fluid. Each inlet has a flared bellmouth inlet portion. The turbine engine component may further have a dirt funnel at the tip of the airfoil portion, a platform with at least one beveled edge, and an undercut trailing edge slot.

Claims

1. A turbine engine component comprising:

an airfoil portion;

a plurality of cooling passages within the airfoil portion;

said cooling passages including a first cooling passage for cooling a leading edge portion of said airfoil portion, a second cooling passage for cooling a main body portion of said airfoil portion, and a third cooling passage for cooling a trailing edge portion of said airfoil portion;

said first cooling passage receiving cooling fluid from only a first inlet having a flared bellmouth inlet portion;

said second cooling passage being independent of said first cooling passage and receiving said cooling fluid from only a second inlet having a flared bellmouth inlet portion;

said third cooling passage being independent of said second cooling passage and receiving said cooling fluid from only a third inlet having a flared bellmouth inlet portion and said third cooling passage having a plurality of outlets for cooling a trailing edge of said airfoil portion;

said second cooling passage having a serpentine tip turn and a dirt funnel located in the serpentine tip turn;

a platform and said platform having a plurality of beveled edges to avoid a flowpath step-up;

each said beveled edge being located where flow crosses a platform gap with an adjacent platform of an adjacent turbine component;

a first one of said beveled edges being located along a first side of said platform and a second one of said beveled edges being located along a second side of said platform;

said airfoil portion having a trailing edge and an undercut extending beneath a portion of said trailing edge; and

said undercut being positioned beneath said platform.

2. The turbine engine component of claim 1, wherein each said inlet further has a minimum area adjacent said flared bellmouth inlet portion and a smooth transition region downstream of and adjacent said minimum area to allow cooling air to diffuse.

3. The turbine engine component of claim 1, wherein each said flared bellmouth inlet portion comprises a pair of flared walls which extend along two opposed surfaces of said inlet.

4. The turbine engine component according to claim 1, wherein said undercut is slot shaped.

5. The turbine engine component according to claim 1, wherein said component comprises a turbine blade.

6. The turbine engine component of claim 1, wherein said airfoil portion has a tip with an exterior surface, wherein said second cooling passage has a tip dirt purge hole, wherein said serpentine tip turn has two arcuate surfaces and a surface positioned intermediate said arcuate surfaces, and wherein said surface positioned intermediate said arcuate surfaces is angled with respect to said exterior surface of said tip so as to promote particulate movement toward the tip dirt purge hole.

7. The turbine engine component according to claim 6, wherein said serpentine tip turn surface is at an angle of 15 degrees with respect to said tip.

8. The turbine engine component of claim 6, wherein each said inlet further has a minimum area adjacent said flared bellmouth inlet portion and a smooth transition region adjacent to and downstream of said minimum area and wherein each said flared bellmouth inlet portion comprises a pair of flared walls which extend along two opposed surfaces of said inlet.

9. The turbine engine component of claim 6, further comprising said first one of said beveled edges being located at a front of the platform and said second one of said beveled edges being located at a rear of the platform.

10. The turbine engine component of claim 6, wherein said undercut has a profile with a first radii used at a first portion and a second radii used at a second portion and wherein said second radii forms a lowermost portion of the profile and said first radii forms a region adjacent said lowermost portion.

11. The turbine engine component of claim 10, wherein said first radii is larger than said second radii.

12. The turbine engine component of claim 1, wherein each said bellmouth inlet has a flare angle in the range of from 10 to 35 degrees.

13. The turbine engine component of claim 1, wherein said first one of beveled edges is located adjacent a leading edge of said platform and said second one of said beveled edges is located adjacent a trailing edge of said platform.

14. The turbine engine component of claim 1, wherein at least one of said beveled edges is located on an underside of the platform.

15. The turbine engine component of claim 1, wherein at least one of said beveled edges is located on a top side of the platform.