Airfoil having panels

Patent metadata

Field	Value
Publication number	US-10309226-B2
Application number	US-201615353874-A
Country	US
Kind code	B2
Filing date	Nov 17, 2016
Priority date	Nov 17, 2016
Publication date	Jun 4, 2019
Grant date	Jun 4, 2019

Abstract

An airfoil includes an airfoil section that defines an airfoil profile. The airfoil section includes a panel that forms a portion of the airfoil profile and a core structure to which the panel is secured.

First claim

What is claimed is:

1. An airfoil comprising:
an airfoil section defining an airfoil profile, the airfoil section including
a panel that forms a portion of the airfoil profile, the panel including a geometrically segmented coating section, the geometrically segmented coating section including a wall that has an outer side, the outer side including an array of closed-sided cells defined by cell sidewalls, and a coating disposed in the array of closed-sided cells, and
a core structure to which the panel is secured.

2. The airfoil as recited in claim 1 , wherein the panel includes a first connector and the core structure includes a second connector that is interlocked with the first connector in a joint that secures the panel to the core structure.

3. The airfoil as recited in claim 2 , wherein one of the first connector and the second connector includes a dovetail and the other of the first connector and the second connector includes a doveslot.

4. The airfoil as recited in claim 1 , wherein the panel includes an internal passage.

5. The airfoil as recited in claim 1 , wherein the panel is ceramic and the core structure is metal.

6. The airfoil as recited in claim 5 , wherein the core structure includes an exterior wall that forms a portion of the airfoil profile.

7. The airfoil as recited in claim 6 , wherein the exterior wall forms a trailing end of the airfoil profile.

8. The airfoil as recited in claim 1 , wherein the panel includes an internal passage, an external wall that borders the internal passage, and a cooling hole that extends through the external wall and that opens to the internal passage.

9. The airfoil as recited in claim 1 , further comprising an additional panel that forms a different portion of the airfoil profile and that is also secured to the core structure.

10. The airfoil as recited in claim 9 , wherein the panel and the additional panel have different compositions.

11. The airfoil as recited in claim 9 , wherein the panel is located adjacent the additional panel, the panel and the additional panel defining a cooling hole at an edge interface there between.

12. The airfoil as recited in claim 9 , wherein the panel and the additional panel together form at least a portion of a leading end of the airfoil profile.

13. The airfoil as recited in claim 1 , wherein the core structure includes an internal passage.

14. The airfoil as recited in claim 1 , wherein the coating is a ceramic material selected from the group consisting of zirconia, hafnia, gatolinia, gatolinia zirconate, molybdate, alumina, and combinations thereof.

15. The airfoil as recited in claim 14 , wherein the closed-sided cell are closed-sided cells.

16. The airfoil as recited in claim 14 , further comprising an additional panel that forms a different portion of the airfoil profile and that is also secured to the core structure, and the additional panel is formed of a monolithic ceramic or a ceramic matrix composite.

17. A gas turbine engine comprising:
a compressor section;
a combustor in fluid communication with the compressor section; and
a turbine section in fluid communication with the combustor,
at least one of the turbine section or the compressor section including an airfoil having an airfoil section defining an airfoil profile, the airfoil section including
a panel that forms a portion of the airfoil profile, the panel including a geometrically segmented coating section, the geometrically segmented coating section including a wall that has an outer side, the outer side including an array of polygonal cells defined by cell sidewalls, and a coating disposed in the array of polygonal cells, and
a core structure to which the panel is secured.

18. The gas turbine engine as recited in claim 17 , wherein the panel includes a first connector and the core structure includes a second connector that is interlocked with the first connector in a joint that secures the panel to the core structure, one of the first connector and the second connector includes a dovetail and the other of the first connector and the second connector includes a doveslot, and the panel includes an internal passage.

19. The airfoil as recited in claim 18 , wherein the core structure includes an exterior wall that forms a portion of the airfoil profile, the panel is ceramic, and the core structure is metal.

20. A method of assembling an airfoil, the method comprising:
securing a panel to a core structure to form an airfoil section, wherein the airfoil section has an airfoil profile and the panel defines a portion of the airfoil profile, the panel including a geometrically segmented coating section, the geometrically segmented coating section including a wall that has an outer side, the outer side including an array of closed-sided cells defined by cell sidewalls, and a coating disposed in the array of closed-sided cells.

21. The method as recited in claim 20 , wherein the panel includes a first connector and the core structure includes a second connector, and the securing includes mating the first connector and the second connector together.

22. The method as recited in claim 21 , wherein one of the first connector and the second connector includes a dovetail and the other of the first connector and the second connector includes a doveslot.

Assignees

• United Technologies Corp

Inventors

• Surace Raymond

Classifications

• F01D9/041

  using blades (F01D5/148 takes precedence) · CPC title

• F01D5/282

  Selecting composite materials, e.g. blades with reinforcing filaments · CPC title

• F01D5/284

  Selection of ceramic materials · CPC title

• F05D2260/202

  by film cooling · CPC title

• F05D2230/60

  Assembly methods · CPC title