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US 7,887,929 B2Granted
Oriented fiber ceramic matrix composite abradable thermal barrier coating
AssigneeUnited Technologies Corporation
InventorsChristopher W. Strock, Susan M. Tholen
Life of this patent
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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.
Claims16
A thermal barrier layer comprising:
- a ceramic member defining a plane that is non-intersecting with a centerline of a gas turbine engine, the ceramic member having ceramic fibers disposed within a ceramic matrix such that the ceramic fibers are oriented substantially perpendicular to the plane, wherein at least one of the ceramic matrix or the ceramic fibers comprises stabilized zirconia, yttria stabilized zirconia or gadolinia zirconate, and a ratio of a percent theoretical density of the ceramic matrix to a volume of the ceramic fibers in the ceramic member is between 0.5 and 16 to control a contribution of the ceramic fibers to the strength of the ceramic member.
Dependencies are inferred from the claim text.