Abstract: A component for use in a gas turbine engine includes a component body, and a damage-indicative coating. The damage-indicative coating is configured to change from an intact state in which the damage-indicative coating has a first appearance to a damaged state in which the damage-indicative coating has a second appearance.

Abstract: A component for use in a gas turbine engine includes a component body, and a damage-indicative coating. The damage-indicative coating is configured to change from an intact state in which the damage-indicative coating has a first appearance to a damaged state in which the damage-indicative coating has a second appearance.

Abstract: A ceramic matrix composite component for use in a gas turbine engine and method for making the same are described herein. The component includes a body and an outer region. The body includes a silicon containing ceramic composite. The outer region is on an outer surface of the body.

Abstract: A ceramic matrix composite component and methods of making are described herein. The ceramic matrix composite may include a silicon containing matrix and refractory fibers embedded within the silicon containing matrix. The ceramic matrix composite component may further include a silicide layer sandwiched between the silicon containing matrix and the refractory fibers. A method of forming a ceramic matrix composite may include infiltrating a fluid that includes a refractory metal element containing compound into a fiber preform that includes fibers. The method may further include depositing the refractory metal element from the refractory metal element containing compound onto the fibers and forming, from the refractory metal element deposited onto the fibers, a refractory metal silicide.

Abstract: A ceramic matrix composite component for use in a gas turbine engine and method for making the same are described herein. The component includes a body and an outer region. The body includes a silicon containing ceramic composite. The outer region is on an outer surface of the body.

Abstract: A method of forming a ceramic matrix composite are described herein. The method may include infiltrating a fiber preform with a solution comprising a refractory precursor in solution with a solvent. The refractory precursor may include a compound having at least one refractory metal element. The method may further include removing the solvent from the fiber preform, and reducing the refractory precursor to form a refractory metal that includes the refractory metal element.

Abstract: A ceramic matrix composite component and methods of making are described herein. The ceramic matrix composite may include a silicon containing matrix and refractory fibers embedded within the silicon containing matrix. The ceramic matrix composite component may further include a silicide layer sandwiched between the silicon containing matrix and the refractory fibers. A method of forming a ceramic matrix composite may include infiltrating a fluid that includes a refractory metal element containing compound into a fiber preform that includes fibers. The method may further include depositing the refractory metal element from the refractory metal element containing compound onto the fibers and forming, from the refractory metal element deposited onto the fibers, a refractory metal silicide.

Abstract: A method of forming a ceramic matrix composite are described herein. The method may include infiltrating a fiber preform with a solution comprising a refractory precursor in solution with a solvent. The refractory precursor may include a compound having at least one refractory metal element. The method may further include removing the solvent from the fiber preform, and reducing the refractory precursor to form a refractory metal that includes the refractory metal element.