Various embodiments include a dense abradable coating, a method of reducing rub damage to a turbine engine part by applying the dense abradable coating thereto, and a turbine engine part having the abradable coating thereon. Particular embodiments include a dense abradable coating including a pore-free metallic composite, a high-aluminum containing brittle alloy, and a plurality of hollow abradable particles.

Various embodiments include a dense abradable coating, a method of reducing rub damage to a turbine engine part by applying the dense abradable coating thereto, and a turbine engine part having the abradable coating thereon. Particular embodiments include a dense abradable coating including a pore-free metallic composite, a high-aluminum containing brittle alloy, and a plurality of hollow abradable particles.

A part made of coated composite material, includes a substrate made of ceramic matrix composite material; a tie-coat layer covering the substrate; and a protective coating on the tie-coat layer and defining an environmental barrier, the protective coating including a rare-earth silicate and including a first outer region including an outer surface of the protective coating opposite to the substrate and having a first working creep, having deformation of less than or equal to 0.07% when a compressive stress of at least 50 MPa is applied for a duration of 10 hours at a temperature of between 1050 C. and 1300 C. The first region includes a grain growth inhibitor; and a second, inner, environmental barrier region, including an interface of the protective coating with the tie-coat layer and having a second working creep.

A part made of coated composite material, includes a substrate made of ceramic matrix composite material; a tie-coat layer covering the substrate; and a protective coating on the tie-coat layer and defining an environmental barrier, the protective coating including a rare-earth silicate and including a first outer region including an outer surface of the protective coating opposite to the substrate and having a first working creep, having deformation of less than or equal to 0.07% when a compressive stress of at least 50 MPa is applied for a duration of 10 hours at a temperature of between 1050 C. and 1300 C. The first region includes a grain growth inhibitor; and a second, inner, environmental barrier region, including an interface of the protective coating with the tie-coat layer and having a second working creep.