High strength joints in ceramic matrix composite preforms

摘要

A joint between a first preform component and a second preform component that are constructed for ultimate use in a gas turbine engine is disclosed. A plurality of extended fibers may be integral with the first preform component and be at least partially enveloped by the second preform component. A method for making the component is also disclosed. In one embodiment the method provides a first preform component having extended fibers integral therewith, and supplying a second preform component. The method further includes inserting the extended fibers at least partially into the second preform component body.

主权项

1. An apparatus comprising:
a gas turbine engine component construction suitable for operational use in an operating environment associated with a gas turbine engine, the component construction including a first ceramic matrix composite preform component comprising a first end surface and a second ceramic matrix composite preform component comprising a second end surface, the first composite preform component including a plurality of extended fibers having an extended portion that protrudes away from the first end surface, the extended fibers received within an internal space of a body of the second composite preform component such that the body of the second composite preform component at least partially envelopes the extended portion of the plurality of extended fibers and creates a joint between the first composite preform component and the second composite preform component at an interface of the first end surface and the second end surface; and wherein the extended fibers are woven into the first ceramic matrix composite preform but not woven into the second ceramic matrix composite preform.