Component For A Gas Turbine Engine

Abstract: A component (100) for a gas turbine engine includes a first surface (102) and a second surface (104). The component (100) additionally includes one or more layers of ceramic matrix composite material extending between the first and second surface (104)s. A thermal void (110) extends between a first end (112) and a second end (114). The second end (114) of the thermal void (110) is a terminal end embedded in the component (100) between the first and second surface (104).

Patent Information

Applicants

Inventors

Specification

Documents