Turbine blades, turbine assemblies, and methods of manufacturing turbine blades

• US 8,777,567 B2
• Filed: 09/22/2010
• Issued: 07/15/2014
• Est. Priority Date: 09/22/2010
• Status: Active Grant

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Poon, Kin, Malak, Malak Fouad, Riahi, Ardeshir, Chou, David
• Primary Examiner(s): Look, Edward
• Assistant Examiner(s): GRIGOS, WILLIAM G
• Application Number:
  US12/888,202
• Publication Number:
  US 20120070307A1
• Time in Patent Office: 1,392 Days
• Field of Search: 415/173.1, 415/173.2, 415/173.3, 415/173.4, 415/914, 416/92, 416/229, 416/235, 416/236.R, 416/97.R, 298/897, 298/897.21
• US Class Current: 416/92
• 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: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft
• CPC Class Codes: Y10T 29/49341 with cooling passage

Abstract

A turbine blade includes a first side wall including a first tip edge, a second side wall opposite the first side wall and including a second tip edge, a tip wall between the first and second side walls, the tip wall recessed from the first tip edge of the first side wall and the second tip edge of the second side wall forming a coolant cavity, a tip recess cavity, a first parapet wall on the first side wall, and a second parapet wall on the second side wall, the coolant cavity defined by the tip wall, and the tip recess cavity defined by the tip wall, and the first and second parapet walls, a step formed between the first tip edge and the tip wall, a cooling hole through the first parapet wall, the step, and the tip wall, the cooling hole including an open and a closed channel section.

Claims

1. A turbine blade, comprising:

a first side wall including a first tip edge;

a second side wall opposite the first side wall and including a second tip edge;

a tip wall extending between the first side wall and the second side wall, the tip wall being recessed from the first tip edge of the first side wall and the second tip edge of the second side wall to form a coolant cavity, a tip recess cavity, a first parapet wall on the first side wall, and a second parapet wall on the second side wall, the coolant cavity defined in part by an interior surface of the tip wall, and the tip recess cavity defined, in part, by a surface of the tip wall, the first parapet wall, and the second parapet wall;

a step formed on only the first side wall, between the first tip edge and the tip wall, the step dividing the first parapet wall into an outer radial section and an inner radial section, the inner radial section defining the step; and

a cooling hole extending through the outer radial section, the step, and the tip wall, the cooling hole including an open channel section and a closed channel section, the open channel section comprising a minority portion of the height of the first parapet wall and extending from the first tip edge of the first parapet wall to the step through only the outer radial section, and the closed channel section extending through the step and the tip wall.

2. The turbine blade of claim 1, wherein the cooling hole has a centerline and the centerline is angled relative to the first tip edge.

3. The turbine blade of claim 2, wherein the centerline is angled relative to the first tip edge at an angle in a range of about 40°

to about 60°

.

4. The turbine blade of claim 2, wherein the centerline is substantially orthogonal to the first tip edge.

5. The turbine blade of claim 2, wherein the centerline has a compound angle to the first tip edge.

6. The turbine blade of claim 1, wherein the open channel section has a first centerline and a portion of the closed channel section has a second centerline that is angled relative to the first centerline.

7. The turbine blade of claim 1, wherein the closed channel section has a first shape and the open channel section has a second shape that is not a portion of the first shape.

8. The turbine blade of claim 1, wherein a first portion of the closed channel section has a first shape, a second portion of the closed channel section and the open channel section form a second shape that is not a portion of the first shape.

9. The turbine blade of claim 1, wherein the first shape comprises a cylinder, and the second shape comprises a frustoconical shape.

10. The turbine blade of claim 1, wherein the step extends along an entire length of the first parapet wall.

11. The turbine blade of claim 1, wherein the cooling hole comprises a plurality of cooling holes, each cooling hole having a largest diameter, and each cooling hole spaced apart from an adjacent cooling hole a distance that is equal to between about three to about eight largest diameters.

12. A turbine rotor comprising:

a rotor; and

a plurality of blades extending radially outwardly from the rotor, each blade comprising;

a first side wall including a first tip edge,

a second side wall opposite the first side wall and including a second tip edge,

a tip wall extending between the first side wall and the second side wall, the tip wall being recessed from the first tip edge of the first side wall and the second tip edge of the second side wall to form a coolant cavity, a tip recess cavity, a first parapet wall on the first side wall, and a second parapet wall on the second side wall, the coolant cavity defined in part by an interior surface of the tip wall, and the tip recess cavity defined, in part, by a surface of the tip wall, the first parapet wall, and the second parapet wall,

a step formed on only the first side wall, between the first tip edge and the tip wall, the step dividing the first parapet wall into an outer radial section and an inner radial section, the inner radial section defining the step, and

a cooling hole extending through the outer radial section, the step, and the tip wall, the cooling hole including an open channel section and a closed channel section, the open channel section comprising a minority portion of the height of the first parapet wall and extending from the first tip edge of the first parapet wall to the step through only the outer radial section, and the closed channel section extending through the step and the tip wall.

13. The turbine rotor of claim 12, wherein the first side wall comprises a convex suction side wall and the second side wall comprises a concave pressure side wall.

14. The turbine rotor of claim 12, wherein the first side wall comprises a concave pressure side wall and the second side wall comprises a convex suction side wall.

15. The turbine rotor of claim 12, wherein the rotor includes a plurality of inlets, and each inlet communicates with a corresponding coolant cavity in the blade.

16. A method of manufacturing a turbine blade comprising:

casting a blade including a first side wall including a first tip edge, a second side wall opposite the first side wall and including a second tip edge, and a tip wall extending between the first side wall and the second side wall, the tip wall being recessed from the first tip edge of the first side wall and the second tip edge of the second side wall to form a coolant cavity, a tip recess cavity, a first parapet wall on the first side wall, and a second parapet wall on the second side wall, the coolant cavity defined in part by an interior surface of the tip wall, and the tip recess cavity defined, in part, by a surface of the tip wall, the first parapet wall, and the second parapet wall;

forming a step on only the first side wall, between the first tip edge and the tip wall, the step dividing the first parapet wall into an outer radial section and an inner radial section, the inner radial section defining the step; and

machining a cooling hole into the blade, wherein the cooling hole extends through the outer radial section, the step, and the tip wall, the cooling hole includes an open channel section and a closed channel section, the open channel section comprising a minority portion of the height of the first parapet wall and extending from the first tip edge of the first parapet wall to the step through only the outer radial section, and the closed channel section extends through the step and the tip wall.

17. The method of claim 16, wherein the step of forming the step comprises casting the step with the blade.

18. The method of claim 16 wherein the step of casting comprises performing a lost wax casting process to form the blade.

19. The method of claim 16, wherein the step of forming the step comprises electrodischarge machining the step into the blade.

20. The method of claim 16, wherein the steps of forming the step and machining the cooling hole comprise laser sintering the step and the cooling hole into the blade.