Method of forming load bearing insert and insert for ceramic matrix composite turbine components
AssigneeRtx Corporation
InventorsChristian X. Campbell, Rutva A. Patel, Justin C. Pratt, Joshua Ramer
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Abstract
A method of forming a gas turbine engine component includes the steps of forming a component shape from a plurality of fabric layers of ceramic matrix composite. The component has an outer surface. An insert is formed from a plurality of fabric layers of ceramic matrix composites into a cup-shaped intermediate insert. The intermediate insert member is densified. Then a final insert is inserted between radially outer layers and radially inner layers on the outer surface. The method then densifies the component. A gas turbine engine component and a gas turbine engine are also disclosed.
Claims14
A method of forming a gas turbine engine component comprising the steps of:
- forming a vane component shape from a plurality of fabric layers of ceramic matrix composite, the vane component shape having an airfoil, a radially outer platform and a radially inner platform, the radially outer platform formed of radially outward ones of the plurality of fabric layers and the radially inner layers also formed from some of the plurality of fabric layers;
- forming an insert from a plurality of insert fabric layers of ceramic matrix composite into an intermediate insert to form a final insert;
- densifying the intermediate insert to form a final insert;
- then, inserting the final insert between the radially outward ones of the plurality of fabric layers and the radially inner layers that form the outer platform to form a combined vane component;
- and
- densifying the combined vane component.
Dependencies are inferred from the claim text.