Abstract: A process for manufacturing a turbomachine part coated with a thermal barrier, includes manufacturing the part by additive manufacture; electrophoretic depositing the part of a layer including particles of a ceramic material; consolidating the layer by heat treatment to obtain a ceramic coating.

Abstract: A test specimen for validating operating parameters of a method for the additive manufacturing of a part by laser melting on powder beds includes at least one upper face, at least one lower face and side faces, including a front side face and a rear side face that are substantially on opposite sides from one another. The test specimen has at least one recess opening onto the front and rear side faces, the recess having a substantially triangular cross sectional shape being delimited by three internal faces, including a first lower internal face oriented upwards, a second upper internal face oriented downwards, and a third upper internal face which defines a narrow wall with one other of the side faces, which is inclined.

Abstract: An assembly for a turbomachine including an annular channel designed to form a flow duct for a flow of gas between two turbine stages of the turbomachine. The channel is bounded by a radially inner annular wall and a radially outer annular wall. The walls are connected by hollow arms that extend radially, a support having a radially outer annular part that is located radially outside the outer annular wall of the annular channel, and a radially inner annular part that is located radially inside the inner annular wall of the annular channel. The outer and inner parts of the support are connected by connecting parts that extend radially and pass through one of the hollow arms of the annular channel. The connecting parts may be connected by a connecting partition having a frangible part that ruptures when the mechanical stresses in the connecting partition are above a threshold.

Abstract: A method for producing, by a metal powder injection moulding (MIM) technique, a part formed of at least one metal and/or at least one metal alloy including at least one internal cavity. A green core of a mixture of at least one powder of at least one ceramic and of a thermoplastic binder is used.

Abstract: An assembly for a turbomachine including an annular channel designed to form a flow duct for a flow of gas between two turbine stages of the turbomachine. The channel is bounded by a radially inner annular wall and a radially outer annular wall. The walls are connected by hollow arms that extend radially, a support having a radially outer annular part that is located radially outside the outer annular wall of the annular channel, and a radially inner annular part that is located radially inside the inner annular wall of the annular channel. The outer and inner parts of the support are connected by connecting parts that extend radially and pass through one of the hollow arms of the annular channel. The connecting parts may be connected by a connecting partition having a frangible part that ruptures when the mechanical stresses in the connecting partition are above a threshold.

Abstract: A process for manufacturing a turbomachine part coated with a thermal barrier, includes manufacturing the part by additive manufacture; electrophoretic depositing the part of a layer including particles of a ceramic material; consolidating the layer by heat treatment to obtain a ceramic coating.

Abstract: A test specimen for validating operating parameters of a method for the additive manufacturing of a part by laser melting on powder beds includes at least one upper face, at least one lower face and side faces, including a front side face and a rear side face that are substantially on opposite sides from one another. The test specimen has at least one recess opening onto the front and rear side faces, the recess having a substantially triangular cross sectional shape being delimited by three internal faces, including a first lower internal face oriented upwards, a second upper internal face oriented downwards, and a third upper internal face which defines a narrow wall with one other of the side faces, which is inclined.

Abstract: A process for manufacturing a turbomachine blade of the type having at least one 3D cavity, wherein the blade is produced by a succession of depositions and selective consolidations of layers of a metal additive manufacturing powder based on an alloy of copper and nickel, the alloy including from 2% to 7% of nickel. It also relates to a turbomachine blade, wherein it is manufactured by metal additive manufacturing using the process.