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US 8,475,695 B2Granted
Ceramic composite with integrated compliance/wear layer
AssigneeGeneral Electric Company
InventorsDouglas M. Carper, Suresh Subramanian
Life of this patent
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Abstract
The integral layer provides a ductile interface for attachment locations of a turbine engine component where a metallic surface is adjacent the attachment location. The ductile layer provides a favorable load distribution through the composite at the attachment location, and eliminates the need for a metallic shim.
Claims14
A method of manufacturing a ceramic matrix composite aircraft engine component, the method comprising the steps of:
- providing a plurality of unidirectional prepreg ceramic fiber plies, the plies comprising coated prepreg ceramic fiber tows;
- laying up the plurality of prepreg ceramic fiber plies in a preselected arrangement to form a component shape;
- overlying at least a portion of the outside surface of the component shape with at least one matrix ply;
- heating the component shape to form a preform;
- infiltrating the preform with a carbon containing slurry;
- infiltrating the preform with at least silicon that produces a silicon carbide component to form a ceramic matrix composite component, wherein the component includes an attachment area defining a surface of the component;
- and
- forming an interface layer having an outer side on the attachment area, wherein the interface layer comprises at least one compound selected from the group consisting of silicon carbide, molybdenum disilicide, boron nitride and alloys thereof, the interface layer having a higher concentration of silicon carbide facing toward the matrix ply compared to the outer side of the interface layer;
- and
- integrating the interface layer and the attachment.
7 more elements
A method of manufacturing a ceramic matrix composite aircraft engine component, the method comprising the steps of:
- laying up a plurality of prepreg ceramic fiber plies in a preselected arrangement to form a component shape;
- overlying at least a portion of the outside surface of the component shape with at least one matrix ply;
- heating the component shape to form a preform;
- infiltrating the preform with a carbon containing slurry;
- infiltrating the preform with at least silicon that produces a silicon carbide component;
- and
- forming an interface layer having an outer side on an attachment area of the preform to form a ceramic matrix composite aircraft engine component;
- wherein the interface layer comprises at least one compound selected from the group consisting of silicon carbide, molybdenum disilicide, boron nitrate and alloys thereof, the interface layer having a higher concentration of silicon carbide facing toward the matrix ply compared to the outer side of the interface layer.
5 more elements
Dependencies are inferred from the claim text.