TURBINE ROTOR BLADES WITH IMPROVED TIP PORTION COOLING HOLES

• US 20150104326A1
• Filed: 10/16/2013
• Published: 04/16/2015
• Est. Priority Date: 10/16/2013
• Status: Active Grant

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Waldman, David, Morris, Mark C., Malak, Malak Fouad
• Granted Patent: US 9,879,544 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 2230/00 Manufacture
• CPC Class Codes: F05D 2260/20 Heat transfer, e.g. cooling
• 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 rotor blade is provided for a turbine section of an engine. The turbine rotor blade includes a platform and an airfoil extending from the platform into a mainstream gas path of the turbine section. The airfoil includes a first side wall; a second side wall joined to the first side wall at a leading edge and a trailing edge; a tip cap extending between the first side wall and the second side wall; a first parapet wall extending from the first side wall; and a first cooling hole through the tip cap and the first parapet wall configured to deliver cooling air. The first cooling hole has a closed channel section and an open channel section. The open channel section forms a slot.

Claims

1. A turbine rotor blade for a turbine section of an engine, the turbine rotor blade comprising:

a platform; and

an airfoil extending from the platform into a mainstream gas path of the turbine section, the airfoil comprising

a first side wall;

a second side wall joined to the first side wall at a leading edge and a trailing edge;

a tip cap extending between the first side wall and the second side wall;

a first parapet wall extending from the first side wall; and

a first cooling hole through the tip cap and the first parapet wall configured to deliver cooling air, the first cooling hole having a closed channel section and an open channel section, the open channel section forming a slot.

2. The turbine rotor blade of claim 1, wherein the first parapet wall is defined by a first axial surface on a first side facing the tip cap, a radial tip edge, and a second axial surface on a second side opposite the tip cap, and wherein the open channel section is open relative to the first axial surface.

3. The turbine rotor blade of claim 2, wherein the airfoil further comprises a step extending in a chordwise direction and formed between the first axial surface of the first parapet wall and the tip cap, the step having a radial step surface and axial step surface.

4. The turbine rotor blade of claim 3, wherein the first cooling hole transitions from the closed channel section to the open channel section at a distance from the radial step surface.

5. The turbine rotor blade of claim 4, wherein the slot has at least two straight edges.

6. The turbine rotor blade of claim 5, wherein the closed channel section is a first closed channel section and the open channel section is a first open channel section, and wherein the airfoil further comprises a second cooling hole with a second closed channel section and a second open channel section, the second open channel section having a cylindrical cross-sectional shape.

7. The turbine rotor blade of claim 6, wherein second cooling hole extends through the radial step surface.

8. A method for manufacturing a turbine rotor blade, comprising the steps of:

forming the turbine rotor blade including a tip portion with a first parapet wall, a second parapet wall, a tip cap extending between the first and second parapet walls, and a cooling channel at least partially defined by the tip cap;

forming a step between the first parapet wall and the tip cap;

forming an initial hole with a longitudinal axis by inserting a tool from a tip edge on the first parapet wall to the cooling channel;

removing the tool along the longitudinal axis of the initial hole to a height approximately equal to the step; and

removing the tool from the first parapet wall in a generally axial direction to form a cooling hole.

9. The method of claim 8, wherein the step of forming the initial hole includes forming a closed channel section and wherein the step of removing the tool from the first parapet wall includes forming an open channel section such that the cooling hole includes the closed channel section and the open channel section.

10. The method of claim 9, wherein the step of removing the tool from the first parapet wall includes forming the open channel section as a slot.

11. The method of claim 10, wherein the step of removing the tool from the first parapet wall includes forming the slot with straight edges.

12. The method of claim 10, wherein the step of removing the tool from the first parapet wall includes forming the open channel section through a side surface of the first parapet wall.

13. The method of claim 8, wherein the step of forming the initial hole includes forming the initial hole at a distance from a radial surface of the step.

14. The method of claim 8, wherein the initial hole is a first initial hole and the cooling hole is a first cooling hole, wherein the method further comprises

forming a second cooling hole extending from the tip edge on the first parapet wall, through a radial surface of the step, and to the cooling channel.

15. A method for manufacturing a turbine rotor blade, comprising the steps of:

forming the turbine rotor blade including a tip portion with a first parapet wall, a second parapet wall, a tip cap extending between the first and second parapet walls, and a cooling channel at least partially defined by the tip cap;

forming a step between the first parapet wall and the tip cap;

forming an initial hole between a tip edge on the first parapet wall and the cooling channel; and

forming a slot between the initial hole and a side surface of the first parapet wall to result in a first cooling hole.

16. The method of claim 15, wherein the step of forming the initial hole includes forming the initial hole with a longitudinal axis by inserting a tool from a tip edge on the first parapet wall to the cooling channel, and

wherein the step of forming the slot includes removing the tool from the initial hole along the longitudinal axis of the initial hole to a height approximately equal to the step and removing the tool from the first parapet wall in a generally axial direction to form the first cooling hole.

17. The method of claim 16, wherein the step of forming the initial hole includes forming a closed channel section, and wherein the step of removing the tool from the first parapet wall includes forming an open channel section such that the cooling hole includes the closed channel section and the open channel section.

18. The method of claim 17, wherein the step of removing the tool from the first parapet wall includes forming the slot with straight edges.

19. The method of claim 15 wherein the step of forming the initial hole includes forming the initial hole at a distance from a radial surface of the step.

20. The method of claim 19, wherein the cooling hole is a first cooling hole, wherein the method further comprises

forming a second cooling hole extending from the tip edge on the first parapet wall, through a radial surface of the step, and to the cooling channel.