Patent ID: 8323409
Filing Date: 2012-12-04
Classification: C23C

Abstract:
1. A system for forming a gas turbine engine component with a thermal barrier coating comprising: a gas turbine engine component; a component fixture having a shaft and a component mount, the component fixture comprising a base cap and an end cap; the shaft being operative to rotate the component mount, the shaft attached to the base cap; the component mount having a first side oriented to face away from the component, a second side oriented to face the component, and a raised edge extending outwardly from the second side such that the second side and the raised edge define a recess, the component mount extending between the base cap and the end cap; the recess being shaped to at least partially receive the component mounted to the component mount for coating such that a first portion of the component located outside of the recess is positioned for being coated and a second portion of the component received within the recess is masked from being coated.