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US 11,441,430 B2Granted
Airfoil with buffer layer to absorb thermal mismatch
AssigneeRaytheon Technologies Corporation
InventorMichael G. McCaffrey
Life of this patent
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Abstract
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.
Claims22
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.
1 more element
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.
1 more element
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.
6 more elements
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.
1 more element
Dependencies are inferred from the claim text.