Oriented fiber ceramic matrix composite abradable thermal...

Details Oriented fiber ceramic matrix composite abradable thermal... Oriented fiber ceramic matrix composite abradable thermal...

2011-02-15

2011-02-15

Austin, Aaron (Department: 1784)

Stock material or miscellaneous articles

All metal or with adjacent metals

Composite; i.e., plural, adjacent, spatially distinct metal...

C428S632000, C428S472000, C416S24100B, C501S035000, C501S038000

Reexamination Certificate

active

07887929

ABSTRACT:
A method of manufacturing a gas turbine engine component includes the steps of forming a ceramic workpiece having oriented ceramic reinforcement, and severing the ceramic workpiece to produce a ceramic member having a desired orientation of the ceramic reinforcement. The ceramic member is then attached to a turbine engine component as a thermal barrier layer for the turbine engine component.

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