TURBINE BLADES AND METHODS OF MANUFACTURING

• US 20090148305A1
• Filed: 12/10/2007
• Published: 06/11/2009
• Est. Priority Date: 12/10/2007
• Status: Active Grant

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Chou, David, Riahi, Ardeshir, Poon, Kin, Malak, Malak F.
• Granted Patent: US 8,206,108 B2
• Time in Patent Office: Days
• US Class Current: 416/97.R
• CPC Class Codes: F01D 5/147 Construction, i.e. structural features, e.g. of weight-saving hollow blades F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18
• CPC Class Codes: F01D 5/18 Hollow blades, i.e. blades with cooling or heating channels or cavities structure of hollow blades in general F01D5/147; Heating, heat-insulating or cooling means on blades
• 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 2230/10 by removing material
• CPC Class Codes: F05D 2230/211 by precision casting, e.g. microfusing or investment casting
• CPC Class Codes: F05D 2240/307 related to the tip of a rotor blade
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A turbine blade includes a convex suction side wall, a concave pressure side wall, a tip wall, an internal cooling circuit, and a plurality of tip edge channels. The tip wall is recessed from a first tip edge of the suction side wall and a second tip edge of the concave pressure side wall to define a suction side wall tip section and a pressure side wall tip section, and the suction side wall tip section is shorter than the pressure side wall tip section. The internal cooling circuit is formed at least partially between the convex suction side wall, the concave pressure side wall, and the tip wall. The plurality of tip edge channels formed through the first tip edge of the convex suction side wall extend to the internal cooling circuit. Methods of manufacturing turbine blades are also provided.

Claims

1. A turbine blade, comprising:

a convex suction side wall including a first tip edge;

a concave pressure side wall opposite the convex suction side wall and including a second tip edge;

a tip wall extending between the convex suction side wall and the concave pressure side wall and coupling the convex suction side wall to the concave pressure side wall, the tip wall is recessed from the first tip edge of the suction side wall and the second tip edge of the concave pressure side wall to define a suction side wall tip section and a pressure side wall tip section, the suction side wall tip section being shorter than the pressure side wall tip section;

an internal cooling circuit formed at least partially between the convex suction side wall, the concave pressure side wall, and the tip wall; and

a plurality of tip edge channels formed through the first tip edge of the convex suction side wall that extend to the internal cooling circuit.

2. The turbine blade of claim 1, further comprising:

a plurality of pressure wall openings formed through the concave pressure side wall to communicate with the internal cooling circuit.

3. The turbine blade of claim 2, wherein:

the internal cooling circuit comprises a pressure side flow circuit and a tip flow circuit;

the plurality of tip edge channels are in flow communication with the tip flow circuit; and

the plurality of pressure wall openings are in flow communication with the pressure side flow circuit.

4. The turbine blade of claim 2, wherein the concave pressure side wall has an outer surface and at least one opening of the plurality of pressure wall openings is formed through the concave pressure side wall at an angle relative to the outer surface thereof.

5. The turbine blade of claim 1, wherein the suction side wall tip section is between about 0.05 mm and about 0.40 mm shorter than the pressure side wall tip section.

6. The turbine blade of claim 1, wherein at least one channel of the plurality of tip edge channels has a discharge angle that is non-perpendicular to the first tip edge of the suction side wall.

7. The turbine blade of claim 1, wherein:

the internal cooling circuit comprises a pressure side flow circuit and a tip flow circuit; and

the plurality of tip edge channels are in flow communication with the tip flow circuit.

8. The turbine blade of claim 1, further comprising a plurality of tip wall openings formed in the tip wall in communication with the internal cooling circuit.

9. A turbine blade, comprising:

a convex suction side wall including a first tip edge;

a concave pressure side wall opposite the convex suction side wall and including a second tip edge;

a tip wall extending between the convex suction side wall and the concave pressure side wall and coupling the convex suction side wall to the concave pressure side wall, the tip wall recessed from first the tip edge of the suction side wall and the second tip edge of the concave pressure side wall to define a suction side wall tip section and a pressure side wall tip section, the suction side wall tip section being shorter than the pressure side wall tip section;

an internal cooling circuit formed at least partially between the convex suction side wall, the concave pressure side wall, and the tip wall;

a plurality of tip edge channels formed through the first tip edge of the convex suction side wall that extend to the internal cooling circuit; and

a plurality of pressure wall openings formed through the concave pressure side wall to communicate with the internal cooling circuit.

10. The turbine blade of claim 9, wherein:

the internal cooling circuit comprises a pressure side flow circuit and a tip flow circuit;

the plurality of tip edge channels are in flow communication with the tip flow circuit; and

the plurality of pressure wall openings are in flow communication with the pressure side flow circuit.

11. The turbine blade of claim 9, wherein at least one opening of the plurality of pressure wall openings has a discharge angle that is substantially non-perpendicular to the pressure side wall.

12. The turbine blade of claim 9, wherein the suction side wall tip section is between about 0.05 mm and about 0. 40 mm shorter than the pressure side wall tip section.

13. The turbine blade of claim 9, wherein at least one channel of the plurality of tip edge channels has a discharge angle that is substantially non-perpendicular to the tip edge.

14. The turbine blade of claim 9, further comprising a plurality of tip wall openings formed in the tip wall in communication with the internal cooling circuit.

15. A method of manufacturing a turbine blade having an internal cooling circuit and an airfoil shape defined by a convex suction side wall, a concave pressure side wall, a tip wall, a leading edge, a trailing edge, a root and a tip recess, the convex suction side wall, the concave pressure side wall, and the tip wall each including a surface that defines at least a portion of an internal cooling circuit, the convex suction side wall and the concave pressure side wall each having a tip edge, the tip wall recessed from a first tip edge of the suction side wall and a second tip edge of the pressure side wall to define a suction side wall tip section and a pressure side wall tip section, respectively, the suction side wall tip section being shorter in height than the pressure side wall tip section, the method comprising the steps of:

forming cores shaped substantially similarly to the internal cooling circuit and to a portion of the tip recess;

forming the turbine blade around the cores, the blade having an outer surface defined by a convex suction side wall, a concave pressure side wall, a tip wall, a leading edge, a trailing edge, a root and a tip recess, the convex suction side wall, the concave pressure side wall, and the tip wall each including a surface that defines at least a portion of an internal cooling circuit, the convex suction side wall and the concave pressure side wall each having a tip edge, the tip wall spaced apart from the tip edge of the suction side wall and the tip edge of the pressure side wall to define a suction side wall tip section and a pressure side wall tip section;

removing the cores from the turbine blade to expose the internal cooling circuit of the turbine blade;

removing a portion of the tip section of the convex suction side wall such that the suction side wall tip section is shorter in height than the pressure side wall tip section; and

machining at least one tip edge channel through the convex suction side wall from the first tip edge thereof to the internal cooling circuit of the turbine blade.

16. The method of claim 15, further comprising the step of:

machining at least one pressure wall opening through the concave pressure side wall to communicate with the internal cooling circuit.

17. The method of claim 15, wherein the step of removing a portion of the tip section of the suction side wall comprises removing a portion of the tip section of the suction side wall such that the tip section of the suction side wall has a height difference of between about 0.05 mm and about 0.40 mm.

18. The method of claim 15, wherein the step of machining the at least one tip edge channel comprises forming the tip edge channel at discharge angle that is substantially non-perpendicular to the tip edge.

19. The method of claim 15, wherein the flow circuit comprises a pressure side cooling circuit and a tip cooling circuit and the step of machining the at least one tip edge channel comprises machining the plurality of tip edge channels to be in flow communication with the tip cooling circuit.

20. The method of claim 15, further comprising the step of forming a tip wall opening in the tip wall in communication with the internal cooling circuit.