Patent ID: 9291060
Filing Date: 2016-03-22
CPC Classification: B32B,C04B,F01D,F05D,Y10T

Claim Text:
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.