The corrosion and erosion resistance of ceramic heat shield elements is improved by the use of yttrium oxide on aluminum oxide as a layer or substrate material is provided. A heat is disclosed having aluminum oxide in the substrate or as a layer on a substrate, wherein yttrium oxide, particularly only yttrium oxide, is present as the outermost layer, particularly directly on the aluminum oxide.

The invention relates to a refractory ceramic batch for the production of an unformed refractory ceramic batch, the use of a batch of this kind for lining metallurgical melting vessels and also a metallurgical melting vessel which is lined with an unformed refractory ceramic product based on a batch of this kind.

The invention relates to a refractory ceramic batch for the production of an unformed refractory ceramic batch, the use of a batch of this kind for lining metallurgical melting vessels and also a metallurgical melting vessel which is lined with an unformed refractory ceramic product based on a batch of this kind.

A combustor assembly for a gas turbine engine and a method of additively manufacturing the same are provided. A combustor dome includes a combustor wall defining a hole and a circumferential groove defined within the combustor wall around the hole. A floating ferrule assembly is additively manufactured with the combustor dome and includes a ferrule positioned at least partially within the hole and defining a radial lip that is received within the circumferential groove to inseparably position the ferrule within the combustor wall. A build support arm is attached to the ferrule by a frangible connecting member, the frangible connecting member being breakable for separating and removing the build support arm from the ferrule.

A combustor assembly for a gas turbine engine and a method of additively manufacturing the same are provided. A combustor dome includes a combustor wall defining a hole and a circumferential groove defined within the combustor wall around the hole. A floating ferrule assembly is additively manufactured with the combustor dome and includes a ferrule positioned at least partially within the hole and defining a radial lip that is received within the circumferential groove to inseparably position the ferrule within the combustor wall. A build support arm is attached to the ferrule by a frangible connecting member, the frangible connecting member being breakable for separating and removing the build support arm from the ferrule.

A flow element for fluidic contact with a hot gas flow inside an aircraft engine includes: a base material, which has a hot gas surface that faces the gas flow and a remote surface that is remote from the gas flow, the base material being completely surrounded by a chroming layer on the hot gas surface and on the remote surface; an adhesive layer on the chroming layer in first portions; an alitising layer, the alitising layer being arranged on the adhesive layer in the first portions; and a thermal barrier layer being arranged on the alitising layer in the first portions. The alitising layer is arranged on the chroming layer in second portions that do not have an adhesive layer, the chroming layer and the alitising layer forming a chroming-alitising layer in the second portions.

A combustor wall is provided for a turbine engine. The combustor wall includes a combustor shell and a combustor heat shield that is attached to the shell. The heat shield includes a first panel and a second panel that sealingly engages the first panel in an overlap joint. A cooling cavity extends between the shell and the heat shield and fluidly couples a plurality of apertures in the shell with a plurality of apertures in the heat shield.

A combustor wall is provided for a turbine engine. The combustor wall includes a combustor shell and a combustor heat shield that is attached to the shell. The heat shield includes a first panel and a second panel that sealingly engages the first panel in an overlap joint. A cooling cavity extends between the shell and the heat shield and fluidly couples a plurality of apertures in the shell with a plurality of apertures in the heat shield.

A combustor for a turbine engine is provided that includes a combustor wall. The combustor wall includes a shell and heat shield, which is attached to the shell. One or more cooling cavities are defined between the shell and the heat shield, and fluidly couple a plurality of apertures defined in the shell with a plurality of apertures defined in the heat shield. The apertures in the heat shield include a first aperture and a second aperture. An angle of incidence between the first aperture and a surface of the heat shield is different than an angle of incidence between the second aperture and the surface.

A combustor for a turbine engine is provided that includes a combustor wall. The combustor wall includes a shell and heat shield, which is attached to the shell. One or more cooling cavities are defined between the shell and the heat shield, and fluidly couple a plurality of apertures defined in the shell with a plurality of apertures defined in the heat shield. The apertures in the heat shield include a first aperture and a second aperture. An angle of incidence between the first aperture and a surface of the heat shield is different than an angle of incidence between the second aperture and the surface.