Abstract: A method applies a titanium aluminide alloy on a substrate. The titanium aluminide alloy has a gamma phase proportion of at least 50% based on an overall composition of the titanium aluminide. The method includes: pretreating a surface of the substrate; heat treating titanium aluminide powder particles at a temperature range of 600° C. to 1000° C. to increase the proportion of the gamma phase; cold spraying the heat-treated powder particles onto the substrate or a part of the substrate to form a layer of titanium aluminide; and thermally post-treating the layer of titanium aluminide applied to the substrate.

Abstract: A method applies a titanium aluminide alloy on a substrate. The titanium aluminide alloy has a gamma phase proportion of at least 50% based on an overall composition of the titanium aluminide. The method includes: pretreating a surface of the substrate; heat treating titanium aluminide powder particles at a temperature range of 600° C. to 1000° C. to increase the proportion of the gamma phase; cold spraying the heat-treated powder particles onto the substrate or a part of the substrate to form a layer of titanium aluminide; and thermally post-treating the layer of titanium aluminide applied to the substrate.

Abstract: A method of repairing a housing part of an aircraft engine. An existing cylindrical bore can be widened to a conical bore or a conical bore can be produced. A filler comprising a material of the same type as a material of the housing part can be prepared. The filler can have a conical peripheral surface configured to fit into the conical bore. The filler can be rotated so that material of the filler and material of the housing part heat up by rotational friction and are plastified. The filler and the housing part can be upset against each other in an axial direction. The filler can be worked so that it finishes flush with the housing part. If a cylindrical bore was initially present, a bore corresponding to the original bore can be produced through the filler.