Substrate with Shaped Cooling Holes and Methods of Manufacture

• US 20130269354A1
• Filed: 05/01/2013
• Published: 10/17/2013
• Est. Priority Date: 10/29/2010
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Starkweather, John Howard, Bennett, William, Gibbons, John, Urbanski, Anthony
• Granted Patent: US 9,696,035 B2
• Time in Patent Office: Days
• US Class Current: 60/754
• CPC Class Codes: B23K 26/0622 by shaping pulses
• CPC Class Codes: B23K 26/384 of specially shaped holes
• CPC Class Codes: B23K 26/388 Trepanning, i.e. boring by moving the beam spot about an axis
• CPC Class Codes: B23K 26/389 of fluid openings, e.g. nozzles, jets laser machining of inkjet nozzles B41J2/1634
• CPC Class Codes: B23K 26/55 for creating voids inside the workpiece, e.g. for forming flow passages or flow patterns
• CPC Class Codes: F23M 5/08 Cooling thereof; Tube walls
• CPC Class Codes: F23R 2900/00018 Manufacturing combustion chamber liners or subparts
• CPC Class Codes: F23R 2900/03041 Effusion cooled combustion chamber walls or domes
• CPC Class Codes: F23R 3/002 Wall structures F23R3/02 and F23R3/007 take precedence
• CPC Class Codes: F23R 3/04 Air inlet arrangements
• CPC Class Codes: F23R 3/06 Arrangement of apertures along the flame tube
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A substrate having one or more shaped effusion cooling holes formed therein. Each shaped cooling hole has a bore angled relative to an exit surface of the combustor liner. One end of the bore is an inlet formed in an inlet surface of the combustor liner. The other end of the bore is an outlet formed in the exit surface of the combustor liner. The outlet has a shaped portion that expands in only one dimension. Also methods for making the shaped cooling holes.

Claims

1. A combustor liner with shaped cooling apertures comprising:

a combustor liner having an inlet surface and an exit surface;

an inlet having a first curvilinear segment, a second curvilinear segment and at least two linear segments;

a bore extending from said inlet aperture toward said exit surface to a transition point;

an outlet extending from said transition point to said exit surface, said outlet having a first curvilinear segment, a second curvilinear segment and at least two linear segments;

said inlet having a first area and said outlet having a second area, wherein said second area is greater than said first area.

2. The combustor liner with shaped cooling apertures of claim 1, said bore disposed at an angle of less than 50 degrees.

3. The combustor liner with shaped cooling apertures of claim 1, said bore disposed as an angle of greater than 5 degrees.

4. The combustor liner with shaped cooling apertures of claim 1, said bore disposed at an angle of about 20 degrees.

5. The combustor liner with shaped cooling apertures of claim 1, said cooling aperture being substantially Y-shaped.

6. The combustor liner with shaped cooling aperture of claim 1 wherein said outlet expands in two directions as compared to said inlet.

7. The combustor liner with shaped cooling aperture of claim 6 wherein said two directions are along one dimension.

8. An aircraft engine component, comprising:

a substrate positioned adjacent an air flow, said substrate having an inlet surface, an outlet surface and a cooling aperture;

said inlet surface having an inlet, said inlet defined by a first curvilinear segment, a second curvilinear segment and first and second linear segments extending between said first and second curvilinear segments;

a bore extending from said inlet toward said outlet surface at a preselected angle;

an outlet formed in said outlet surface defined by a first curvilinear segment, a second curvilinear segment and first and second linear segments extending between said first and second curvilinear segments;

said inlet defining a first area and said outlet defining a second area, wherein said first area is less than said second area; and

wherein said second area expands in a single dimension from said first area to said second area.

9. The aircraft engine component with cooling aperture of claim 8, said bore having a transition point where said first area begins increasing.

10. The aircraft engine component with cooling aperture of claim 9, said cooling aperture having wings between said transition point and said outlet.

11. The aircraft engine component with cooling aperture of claim 8, said inlet being substantially oval in shape.

12. The aircraft engine component with cooling aperture of claim 11, said outlet being substantially oval in shape.

13. A method of forming a shaped cooling hole in a combustor liner, comprising:

drilling a center bore at a center location with a laser from an outlet toward an inlet;

pulsing said laser a first time while moving said laser to a first side of said center location;

stopping said first pulsing and moving said laser to said center location;

pulsing said laser a second time while moving said laser to a second side of said center location;

stopping said second pulsing and moving said laser to said center location;

trepanning said laser to control size and shape of a cooling hole.

14. A method of forming a cooling aperture, comprises:

drilling a center bore at a preselected angle from an exit surface toward an inlet surface through a substrate;

pulsing said laser, a first series while moving one of said laser and said substrate in a first direction relative to a center line of said bore;

stopping said pulsing said laser said first series and moving said one of said laser and said substrate;

pulsing said laser and second series while moving said one of said laser and said substrate in a second direction relative to said center line of said bore;

stopping said pulsing said laser said second series and moving said one of said laser and said substrate;

trepanning said laser to form said substantially oval shaped inlet.

15. The method of forming a cooling aperture of claim 14 further comprising forming a substantially oval shaped inlet.

16. The method of forming a cooling aperture of claim 15, forming said oval shaped outlet with a larger area than said oval shaped inlet.

17. The method of forming a cooling aperture of claim 14, forming a transition point in said bore.