| 摘要 |
<p>The method comprises applying metal powder mixture (16) or metal powder on a prefabricated engine component with or without binder by spraying, and binding and compressing the metal powder mixture or metal powder on the engine component by sintering and/or by filling. The application of the metal powder mixture or metal powder takes place in a preformed condition. The sintering step takes place in a vacuum, under protective gas and in reducing atmosphere. Before applying metal powder mixture or metal powder, an adhesive agent is applied in the area of the later layer on the engine component. The method comprises applying metal powder mixture (16) or metal powder on a prefabricated engine component with or without binder by spraying, and binding and compressing the metal powder mixture or metal powder on the engine component by sintering and/or by filling. The application of the metal powder mixture or metal powder takes place in a preformed condition. The sintering step takes place in a vacuum, under protective gas and in reducing atmosphere. Before applying the metal powder mixture or metal powder, an adhesive agent is applied in the area of the later layer on the engine component, where the adhesive agent is an adhesive layer and is a powder mixture, a metal lattice or a metal film. The finished sintered layer has a thickness of 0.01-20 mm and is an abrasive coating of a gas turbine engine. An independent claim is included for an engine component.</p> |
