Fabrication of composite articles having an infiltrated matrix
AssigneeGeneral Electric Company
InventorsJames D. Steibel, Kenneth P. Onderko
Life of this patent
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Abstract
A composite article is fabricated by preparing a porous first region piece having a first reinforcement material with no matrix, and rigidizing the first reinforcement material to form a porous first coated preform. At least one second-region layer of a second reinforcement material having no matrix is applied in contact with at least a portion of the first coated preform. The second reinforcement material is rigidized, to form a second coated preform. A second-region matrix material is deposited into at least some of the porosity of the second coated preform. The reinforcement material may be silicon carbide fibers, and the infiltrated matrix may be silicon carbide.
Claims17
A method for fabricating a composite article which is a portion of a gas turbine engine, comprising the steps of:
- preparing a porous first-region piece comprising a first reinforcement material having no matrix;
- thereafter
- rigidizing the first reinforcement material to form a porous first coated preform;
- thereafter
- applying at least one second-region layer of a second reinforcement material having no matrix in contact with at least a portion of the first coated preform;
- thereafter
- rigidizing the second reinforcement material, to form a second coated preform;
- and thereafter
- depositing a second-region matrix material into at least some of the porosity of the second coated preform to produce the composite article of the second reinforcement material embedded in the second-region matrix material, wherein the composite article is a portion of a gas turbine engine.
A method for fabricating a composite article which is a portion of a gas turbine engine, comprising the steps of:
- providing a mandrel whose outer surface defines at least a portion of an inner cavity surface of the article;
- applying at least one insert layer of a first reinforcement material overlying the mandrel;
- rigidizing the first reinforcement material to form a porous first coated preform;
- removing the mandrel from the first coated preform;
- applying at least one shell layer of a second reinforcement material overlying the first coated preform to form a porous shell;
- rigidizing the second reinforcement material;
- and
- depositing a matrix material into the porosity of the porous first coated preform and the porous shell to produce the composite article of the first reinforcement material and the second reinforcement material embedded in the matrix material, wherein the composite article is a portion of a gas turbine engine.
A method for fabricating a composite article, comprising the steps of:
- preparing a porous first-region piece comprising a first reinforcement material having no matrix;
- thereafter
- rigidizing the first reinforcement material to form a porous first coated preform;
- thereafter
- depositing a first-region matrix material into at least some of the porosity of the first coated preform to form an infiltrated first coated preform;
- thereafter
- applying at least one second-region layer of a second reinforcement material having no matrix in contact with at least a portion of the infiltrated first coated preform;
- thereafter
- rigidizing the second reinforcement material, to form a second coated preform;
- and thereafter
- depositing a second-region matrix material into at least some of the porosity of the second coated preform.
Dependencies are inferred from the claim text.