The present invention relates to a component of a turbomachine with a repair layer and a method for repairing wear-damaged components (1, 10) of a turbomachine, in particular of elements of a flow duct boundary, having the following method steps: preparing the area to be repaired, in order to provide a smooth and clean surface (4), applying an Ni-based braze (7) with a proportion of hard material particles (8) to the surface (4) to form a repair layer (15), wherein the hard material particles comprise hard alloys based on cobalt or nickel, heat treating the component to braze the repair layer onto the component under vacuum conditions.

An airfoil includes a first airfoil piece and a second airfoil piece bonded to the first airfoil piece at a joint. The first airfoil piece and the second airfoil piece are formed of aluminum alloys. At least one of the aluminum alloys is an aluminum alloy composition that has greater than 0.8% by weight of zinc.

A method includes heating a brazing material in a braze chamber of a first component to a braze temperature to melt the brazing material. The brazing material flows from the braze chamber, through at least one internal channel of the first component, and into a braze gap between the first component and a second component to braze the first component to the second component. A brazed article includes a first component having a braze chamber and at least one internal channel extending from the braze chamber to an external surface, a second component having at least one braze surface separated from the external surface of the first component by a braze gap, and a braze material in the braze gap. A braze assembly includes a first component, a second component, and a brazing material in the braze chamber.

A blade for a turbomachine, a tip for a blade of a turbomachine and a related method are disclosed. The blade may include a tip body having a shape at least partially configured for coupling to an airfoil body of the blade; at least one coolant passage in the tip body configured for fluid communication with at least one coolant passage in the airfoil body; and a retention member extending from the tip body for coupling to a tip retention member seat in the airfoil body. The tip can be replaced, allowing for changes in the coolant passages in the tip of a blade.

The present disclosure relates to a method of manufacturing composite airfoils bonded to a metallic root. A composite body may be formed with a metallic co-molded member. The co-molded member may be transient liquid phase (TLP) bonded to a metallic root. The metallic root may allow the composite body to be attached to a rotor. The airfoil may also have a metallic edge which is TLP bonded to the composite body via a co-molded edge.

An assembly for a dual-walled component of a gas turbine engine and methods of forming and repairing a dual-walled component. The assembly includes a cold section part having an outer surface that defines a plurality of impingement apertures, a hot section part including a pre-sintered preform, the hot section part positioned over the outer surface of the cold section part, and a plurality of support structures including the pre-sintered preform, the plurality of support structures positioned between the hot section part and the cold section part, the plurality of support structures separating the hot section part from the cold section part to define at least one cooling channel therebetween.

System (10) and methods (1000) for structural braze repair of high gamma prime nickel base gas turbine components (1). The system may include a controller (200) operably connected to a heating system (100), e.g., a vacuum furnace, for controlling heat temperatures of the furnace for a specified or predetermined time period. A damaged component is placed in the furnace and heated to a first temperature, which is held for the specified time period before being cooled to about room temperature. The component is then heated to a second temperature higher than the first temperature, which is held for a second time period before being cooled again to about room temperature. After cooling the component may be braze repaired at a third temperature equal to or higher than the previous temperatures for a third time period.

A method of welding a superalloy component includes the following sequential steps. A welding step for welding a cavity using a filler metal in an inert atmosphere, where the cavity is located in the component. A covering step for covering the filler metal and a portion of the component with a weld filler layer in the inert atmosphere. The weld filler layer has a greater ductility than material comprising the component and/or material comprising the filler metal. A second covering step for covering the weld filler layer with a braze material, and subsequently performing a brazing operation. A heat treating step heat treats the component.

A component including a channel and an insert is provided. The channel is configured to extend through a wall thickness of the component from an inner surface of the component to an outer surface of the component. The channel is defined by an inner channel surface. The insert is configured to permit flow cooling fluid such as air and has an outer insert surface corresponding to and attached to the inner channel surface. The component may be a turbine component. Also provided is a method for forming the component.

In some embodiments, a process treats a turbine component. The turbine component includes an article and a wear component brazed to the article. The process includes applying a braze tape on at least a portion of the wear component and thermal processing the turbine component while the braze tape is on the at least a portion of the wear component to treat the turbine component. In some embodiments, an assembly includes a turbine component. The turbine component includes an article and a pre-sintered preform brazed to a surface of the article. The assembly also includes a braze tape on at least a portion of the pre-sintered preform. In some embodiments, a treated turbine component includes a treated article and a pre-sintered preform brazed to a surface of the treated article. The treated turbine component has been thermally processed with the pre-sintered preform being substantially free of re-flow.