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US 11,697,994 B2Granted
CMC component with cooling protection
AssigneeRaytheon Technologies Corporation
InventorsMichael G. McCaffrey, Bryan P. Dube
Life of this patent
Estimating the term…
Abstract
A gas turbine engine component includes a ceramic matrix composite (CMC) body that includes an interior surface that defines a blind cavity. A barrier coating is disposed on an exterior of the CMC body. A ceramic body in the blind cavity lines at least a portion of the interior surface of the CMC body. The ceramic body defines an open, interconnected network of pores.
Claims13
A gas turbine engine component comprising:
- a ceramic matrix composite (CMC) body including an interior surface defining a blind cavity having only one opening;
- a barrier coating disposed on an exterior of the CMC body;
- and
- a ceramic body in the blind cavity and lining at least a portion of the interior surface of the CMC body, the ceramic body defining an open, interconnected network of pores.
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 (CMC) airfoil body defining leading and trailing ends and first and second sides that join the leading and trailing ends, the CMC airfoil body including an interior surface defining a radially-extending blind cavity having only one opening,
- a barrier coating disposed on an exterior of the CMC airfoil body, and
- a ceramic body in the radially-extending blind cavity and lining at least a portion of the interior surface of the CMC airfoil body, the ceramic body defining an open, interconnected network of pores.
5 more elements
Dependencies are inferred from the claim text.