Airfoil with buffer layer to absorb thermal mismatch
An airfoil includes a ceramic matrix composite airfoil core that defines an airfoil portion and a root portion. The ceramic matrix composite airfoil core is subject to core thermal growth. A platform includes a ceramic matrix composite that wraps around the root portion. The platform is subject to platform thermal growth. A buffer layer is located between the root portion and the platform. The buffer layer absorbs a mismatch between the core thermal growth and the platform thermal growth.
1. An airfoil comprising:
a ceramic matrix composite airfoil core defining an airfoil portion and a root portion;
a ceramic matrix composite wrapping around the root portion; and
a frangible layer between the root portion and the ceramic matrix composite wrapping, the frangible layer having a compressive strength that is below a stress produced from a difference in thermal growth between the root portion and the ceramic matrix composite wrapping with the root portion at 300° C. to 700° C. and the airfoil portion at 600° C. to 1300° C.
2. The airfoil as recited in claim 1 , wherein the root portion has axial faces and circumferential faces, the frangible layer is on the axial faces.
3. The airfoil as recited in claim 2 , wherein the frangible layer wraps around edges of the axial face onto localized portions of the circumferential faces, and a remainder of the circumferential faces exclude the frangible layer.
4. The airfoil as recited in claim 1 , wherein the frangible layer has a thickness of 0.02 millimeters to 0.4 millimeters.
5. The airfoil as recited in claim 1 , wherein the frangible layer is a ceramic coating and is selected from the group consisting of alumina, silicon carbide, and combinations thereof.
6. The airfoil as recited in claim 1 , wherein the frangible layer includes hollow spheres disposed in a matrix.
7. The airfoil as recited in claim 6 , wherein the matrix is selected from the group consisting of alumina, silicon carbide, and combinations thereof.
8. The airfoil as recited in claim 1 , wherein the ceramic matrix composite wrapping defines a platform.
9. The airfoil as recited in claim 1 , wherein the compressive strength is less than 25 MPa.
10. The airfoil as recited in claim 9 , wherein the frangible layer has a porosity, by volume percent, of 50% to 90%.
11. The airfoil as recited in claim 10 , wherein the frangible layer is selected from the group consisting of alumina, silicon carbide, silicon nitride, boron carbide, elemental silicon, and combination thereof.
12. The airfoil as recited in claim 11 , wherein the compressive strength is less than 5 MPa.
13. An airfoil comprising:
a fiber-reinforced composite airfoil core defining an airfoil portion and a root portion, the root portion defining axial faces and circumferential faces, and the fiber-reinforced composite airfoil core being subject to core thermal growth;
fiber-reinforced composite wrapping around the root portion, the fiber-reinforced composite wrapping being subject to wrapping thermal growth; and
a buffer layer on the axial faces between the root portion and the fiber-reinforced composite wrapping, the buffer layer wrapping around edges of the axial faces onto localized portions of the circumferential faces, and a remainder of the circumferential faces excluding the buffer layer, the buffer layer absorbing a mismatch between the core thermal growth and the platform thermal growth.
14. The airfoil as recited in claim 13 , wherein the buffer layer is a coating.
15. The airfoil as recited in claim 14 , wherein the coating is selected from the group consisting of alumina, silicon carbide, and combinations thereof.
16. The airfoil as recited in claim 13 , wherein the buffer layer includes hollow spheres disposed in a matrix.
17. The airfoil as recited in claim 16 , wherein the matrix is selected from the group consisting of alumina, silicon carbide, and combinations thereof.
18. The airfoil as recited in claim 13 , wherein the buffer layer has a compressive strength of less than 25 MPa and a porosity, by volume percent, of 50% to 90%.
19. 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,
the turbine section having an airfoil that includes
a ceramic matrix composite airfoil core defining an airfoil portion and a root portion,
the root portion defining axial faces and circumferential faces,
a ceramic matrix composite wrapping around the root portion, and
a buffer layer on the axial faces between the root portion and the ceramic matrix composite wrapping.
20. An airfoil comprising:
a ceramic matrix composite airfoil core defining an airfoil portion and a root portion, the root portion defining axial faces;
a ceramic matrix composite wrapping around the root portion; and
a frangible layer between the ceramic matrix composite wrapping and at least the axial faces of the root portion, the frangible layer crushing into fractured pieces under compressive stress due to differential thermal expansion between the ceramic matrix composite wrapping and the root portion and thereby providing an expansion gap for differential thermal growth displacement between the ceramic matrix composite wrapping and the root portion.
21. The airfoil as recited in claim 20 , wherein the frangible layer has a thickness of 0.02 millimeters to 0.4 millimeters.
22. The airfoil as recited in claim 21 , wherein the frangible layer has a porosity, by volume percent, of 50% to 90%.