Abstract: In some examples, a method of forming an article for a gas turbine engine, the method comprising depositing a powder to form a protective coating on a leading edge of an airfoil substrate. The deposited powder includes carbide particles in a metal matrix and the carbide particles in the powder have an average particle size of about 1 micron or less. The protective coating on the leading edge of the airfoil substrate includes the carbide particles in the metal matrix.

Abstract: A suspension plasma spray deposition system comprising a suspension plasma spray device configured to deposit coating material on a surface of a component. The surface of the component includes a plurality of apertures. The system further includes a fluid flow system configured to flow fluid through the plurality of apertures in the surface of the component to reduce deposition of coating material in plurality of apertures. The fluid flow through each respective aperture of the plurality of apertures in the surface of the component is between about 0.095 and about 0.200 cubic feet per minute (cfm).

Abstract: The present disclosure relates generally to blades used in gas turbine engines. More specifically designs in accordance with the present disclosure include turbine blades comprising ceramic matrix composite materials with abrasive tips coupled thereto.

Abstract: The present disclosure relates generally to blades used in gas turbine engines. More specifically designs in accordance with the present disclosure include turbine blades comprising ceramic matrix composite materials with abrasive tips coupled thereto.