A method for coating a substrate surrounding a gas turbine blade, including the following steps: in a first step, a MCrAlY matrix is applied by means of a PVD method; in a further step, an oxide layer is applied by means of a PVD method.

A casing for a gas turbine engine, including: an inner ring portion; an outer ring portion; and a plurality of blunting plates arranged circumferentially between the inner ring portion and the outer ring portion, wherein the plurality of blunting plates are positioned to overlap each other.

A method for limiting void formation in a melt-infiltrated ceramic matrix composite (MI-CMC) component includes arranging one or more infiltrant feedstocks in fluid communication with a targeted area of the MI-CMC component. The one or more infiltrant feedstocks have a nominal melting point at or below a nominal melting point of an alloy within the MI-CMC component. The method includes heating the one or more infiltrant feedstocks to a first temperature at or above the nominal melting point of the one or more infiltrant feedstocks to form a molten phase. The method also includes infiltrating the targeted area of the MI-CMC component with the molten phase. As such, the molten phase reacts with a solid phase in the targeted area of the MI-CMC component. Further, the method includes cooling the MI-CMC component to a second temperature that is below the first temperature to solidify the molten phase.