CELL STRUCTURE THERMAL BARRIER COATING

• US 20120317984A1
• Filed: 06/16/2011
• Published: 12/20/2012
• Est. Priority Date: 06/16/2011
• Status: Abandoned Application

• Current Assignee: United Technologies Corporation (Rtx Corporation)
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: Dierberger, James A.
• Application Number:
  US13/162,009
• Publication Number:
  US 20120317984A1
• Time in Patent Office: Days
• US Class Current: 60/722
• CPC Class Codes: C23C 4/01 Selective coating, e.g. pattern coating, without pre-treatment of the material to be coated
• CPC Class Codes: C23C 4/18 After-treatment
• CPC Class Codes: F05D 2250/283 honeycomb
• CPC Class Codes: F23M 2900/05004 Special materials for walls or lining
• CPC Class Codes: F23M 5/00 Casings; Linings; Walls
• CPC Class Codes: F23M 5/04 Supports for linings
• CPC Class Codes: F23R 2900/00018 Manufacturing combustion chamber liners or subparts
• CPC Class Codes: F23R 3/007 constructed mainly of ceramic components
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A combustor component of a gas turbine engine includes a thermal barrier coating on a substrate, the thermal barrier coating defines a multiple of cells.

Claims

1. A component of a gas turbine engine comprising:

a substrate; and

a thermal barrier coating on said substrate, said thermal barrier coating defines a multiple of cells.

2. The component as recited in claim 1, wherein said substrate defines an offset within each of said multiple of cells.

3. The component as recited in claim 2, wherein said offset within each of said multiple of cells is a post.

4. The component as recited in claim 3, wherein said post within each of said multiple of cells is frustro-conical.

5. The component as recited in claim 3, wherein said post is located within a center of each of said multiple of cells.

6. The component as recited in claim 3, wherein said post defines a height that is approximately two-thirds the thickness of said thermal barrier coating.

7. The component as recited in claim 2, wherein said offset within each of said multiple of cells is a divot.

8. The component as recited in claim 7, wherein said divot is located within a center of each of said multiple of cells.

9. The combustor component as recited in claim 1, wherein each of said multiple of cells are hexagonal in shape.

10. The combustor component as recited in claim 1, wherein each of said multiple of cells are separated by a gap.

11. The combustor component as recited in claim 1, said substrate is a nickel base superalloy.

12. A combustor component of a gas turbine engine comprising:

a substrate which defines a multiple of offsets; and

a thermal barrier coating on said substrate, said thermal barrier coating defines a multiple of cells, each of said multiple of cells correspond with at least one of said multiple of offsets.

13. The combustor component as recited in claim 12, wherein at least one of said multiple of offsets is a post.

14. The combustor component as recited in claim 13, wherein said post is frustro-conical.

15. The combustor component as recited in claim 13, wherein each of said multiple of posts is located within a center of each of said multiple of cells.

16. The combustor component as recited in claim 13, wherein said post is approximately two-thirds the thickness of said thermal barrier coating.

17. The combustor component as recited in claim 12, wherein at least one of said multiple of offsets is a divot.

18. The combustor component as recited in claim 17, wherein s each of said multiple of divots is located within a center of each of said multiple of cells

19. The combustor component as recited in claim 12, wherein each of said multiple of cells are hexagonal in shape.

20. The combustor component as recited in claim 19, wherein each of said multiple of cells are separated by a gap.