A method and apparatus for protecting a furnace floor of a black liquor recovery boiler, where a mixture is formed by mixing material with a fluid, and the furnace floor is covered by said mixture by flowing the formed mixture onto the floor from the outside of the furnace.

An excess enthalpy combustion device includes a furnace body and a feed mechanism disposed on one side of the furnace body. A flue gas outlet is provided on the furnace body. A wall of the furnace body includes a refractory material layer, an electric heating layer, and an insulating layer that are arranged in sequence from inside to outside. Two horizontal first refractory partitions which are staggered in the vertical direction are provided in an upper layer of the furnace body. Four vertical second refractory partitions which are staggered in the horizontal direction are provided in a lower layer of the furnace body; a third refractory partition parallel to a side wall is provided on the other side of the furnace body opposite to a grate mechanism. The combustion device adopts an electric heater to heat the furnace body when the electric heater is powered on.

An excess enthalpy combustion device includes a furnace body and a feed mechanism disposed on one side of the furnace body. A flue gas outlet is provided on the furnace body. A wall of the furnace body includes a refractory material layer, an electric heating layer, and an insulating layer that are arranged in sequence from inside to outside. Two horizontal first refractory partitions which are staggered in the vertical direction are provided in an upper layer of the furnace body. Four vertical second refractory partitions which are staggered in the horizontal direction are provided in a lower layer of the furnace body; a third refractory partition parallel to a side wall is provided on the other side of the furnace body opposite to a grate mechanism. The combustion device adopts an electric heater to heat the furnace body when the electric heater is powered on.

An article such as a heat shield panel includes a substrate and a multi-layered coating supported on the substrate. The multi-layered coating can include alternating layers of different ceramic material compositions having individual thicknesses of less than 25 micrometers.

An article such as a heat shield panel includes a substrate and a multi-layered coating supported on the substrate. The multi-layered coating can include alternating layers of different ceramic material compositions having individual thicknesses of less than 25 micrometers.

A structure is provided for a turbine engine. The structure includes a shell with a first surface, and a heat shield with a textured second surface and a textured third surface. The texture of a portion of the second surface is different than the texture of a portion of the third surface. The first surface and the second surface define a first cooling cavity between the shell and the heat shield. The first surface and the third surface define a second cooling cavity between the shell and the heat shield.

A structure is provided for a turbine engine. The structure includes a shell with a first surface, and a heat shield with a textured second surface and a textured third surface. The texture of a portion of the second surface is different than the texture of a portion of the third surface. The first surface and the second surface define a first cooling cavity between the shell and the heat shield. The first surface and the third surface define a second cooling cavity between the shell and the heat shield.

A wall assembly that may be for a combustor of a gas turbine engine includes a liner having a hot face that defines a combustion chamber, an opposite cold face, and a plurality of effusion holes. A shell of the assembly is spaced outward from the cold face and includes a plurality of impingement holes each having a centerline orientated substantially normal to the cold face. A plurality of cooling member arrays of the liner each include a first plurality of members that may be pins projecting outward from the cold face to conduct heat out of the liner. Each array is spaced between adjacent effusion holes and is symmetrically orientated about the respective centerline.

The invention relates to a combustion chamber module for an aircraft turbine engine, comprising a combustion chamber defined by an internal annular wall and an external annular wall provided with air intake openings, the module further comprising an internal housing and an external housing. According to the invention, at least one of the internal and external housings has, on the surface thereof facing the combustion chamber, a marking system comprising a plurality of different marks angularly spaced apart from each other, each mark being produced facing one of the air intake openings in order to be visible from inside the combustion chamber and each indicating the angular position of a zone of the combustion chamber comprising the air intake opening.

The invention relates to a combustion chamber module for an aircraft turbine engine, comprising a combustion chamber defined by an internal annular wall and an external annular wall provided with air intake openings, the module further comprising an internal housing and an external housing. According to the invention, at least one of the internal and external housings has, on the surface thereof facing the combustion chamber, a marking system comprising a plurality of different marks angularly spaced apart from each other, each mark being produced facing one of the air intake openings in order to be visible from inside the combustion chamber and each indicating the angular position of a zone of the combustion chamber comprising the air intake opening.