Airfoil with panel and side edge cooling
An airfoil includes a core structure that defines a cooling passage, a panel attached with the core structure, and a channel. The panel has an exterior gas path side, an opposed interior side, and side edges. The channel has a first end that opens to the cooling passage and a second end that opens to the exterior gas path side at one of the side edges.
1. An airfoil comprising:
a core structure defining a cooling passage, the core structure including a wall having a wall protrusion defining a wall bearing surface;
a panel attached with the core structure, the panel having an exterior gas path side, an opposed interior side, and side edges, wherein one of the side edges includes a panel protrusion defining a panel bearing surface that abuts the wall bearing surface; and
a channel extending through at least one of the wall protrusion or the panel protrusion, the channel having a first end opening to the cooling passage and a second end opening to the exterior gas path side at one of the side edges.
2. The airfoil as recited in claim 1 , wherein the channel opens to a recess at the one of the side edges.
3. The airfoil as recited in claim 2 , wherein the recess is ramped and blends into the exterior gas path side of the panel.
4. The airfoil as recited in claim 1 , wherein the panel includes a geometric segmented coating section.
5. The airfoil as recited in claim 1 , wherein the panel bearing surface and the wall bearing surface are sloped so as to overlap.
6. The airfoil as recited in claim 1 , wherein the core structure defines a portion of an airfoil profile, and the panel defines another portion of the airfoil profile.
7. The airfoil as recited in claim 1 , wherein the core structure includes at least a portion of an airfoil section and at least a portion of an endwall section, and the panel is attached to the endwall section.
8. The airfoil as recited in claim 1 , wherein the channel extends through the wall protrusion and the panel protrusion.
9. The airfoil as recited in claim 1 , wherein the panel bearing surface and the wall bearing surface are sloped so as to overlap, and the channel extends exclusively through the panel protrusion.
10. The airfoil as recited in claim 1 , wherein the panel bearing surface and the wall bearing surface are sloped so as to overlap, and the channel extends exclusively through the wall protrusion.
11. The airfoil as recited in claim 1 , wherein the panel includes a geometric segmented coating section that has an array of cells defined by cell sidewalls and a coating disposed in the array of cells.
12. The airfoil as recited in claim 11 , wherein the panel bearing surface and the wall bearing surface are sloped so as to overlap.
13. The airfoil as recited in claim 1 , wherein the panel bearing surface abuts the wall bearing surface at a bearing interface, and the channel is a notch that opens at the bearing interface.
14. The airfoil as recited in claim 1 , wherein the panel defines a portion of at least one of a leading end, a trailing end, a pressure side, or a suction side of an airfoil profile.
15. The airfoil as recited in claim 1 , wherein the panel bearing surface is oriented outwards, toward the exterior gas path side of the panel.
16. 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
a core structure defining at least a portion of a cooling passage, the core structure including a wall having a wall protrusion defining a wall bearing surface,
a panel attached with the core structure, the panel having an exterior gas path side, an opposed interior side, and side edges, wherein one of the side edges includes a panel protrusion defining a panel bearing surface that abuts the wall bearing surface, and
a channel extending through at least one of the wall protrusion or the panel protrusion, the channel having a first end opening to the cooling passage and a second end opening to the exterior gas path side at one of the side edges.
17. An article comprising:
a coolant passage;
a panel having an exterior gas path side, an opposed interior side, and a first protrusion;
a mating component having a second protrusion, the first and second protrusions meeting at a bearing interface;
a channel extending through at least one of the first and second protrusions, the channel having a first end opening to the coolant passage and a second end opening to the exterior gas path side, wherein the channel is a notch that opens at the bearing interface.
18. The article as recited in claim 17 , wherein the bearing interface is sloped with respect to a local portion of the exterior gas path side.
19. The article as recited in claim 18 , wherein the channel extends through the first and second protrusions.
20. The article as recited in claim 19 , wherein the mating component is a second panel.