An automated welding system includes a mounting platform, a welding tool, an imaging device configured to acquire data associated with an object, and a controller. The controller is configured to receive the acquired data, determine an area to be welded in the acquired data, retrieve stored master model data associated with the object, and compare the acquired data to the stored master model data to identify a master model area in the acquired data. The controller is also configured to mask the master model area in the acquired data, such that the master model area is excluded from the area to be welded, and generate control instructions for controlling at least one of the mounting platform and the welding tool to weld the area to be welded.

Methods for repairing a trailing edge of an airfoil are provided. The method can include removing a portion of the trailing edge of the airfoil to form an intermediate component, and then applying using additive manufacturing a replacement portion on the intermediate component to form a repaired airfoil. The replacement portion defines at least one trailing edge ejection slot.

A thermoinsulating tile for combustion chambers of gas turbines comprises: a thermoinsulating material body having a first face and a second face; a sealed chamber encapsulated in the thermoinsulating material body between the first face and the second face and containing a marker substance in the liquid state at least at a temperature of use of the thermoinsulating tile.

Example systems may include an energy source, a material delivery device, and a computing device. The computing device, based on a target height of a layer deposited on a component by directed energy deposition, may control an energy source directed at a component and may control a material delivery device. Controlling the energy source may include advancing an energy beam along a first path to form an advancing molten pool on the component. Controlling the material delivery device may include delivering a material to the advancing molten pool. The material may combine with the advancing molten pool to form a first raised track having an actual height. The layer may include the first raised track. A deposited region of the component may include the layer. The actual height may affect a resultant microstructure within the deposited region.

A method for repairing a fuel nozzle guide includes mechanically separating a heat shield of a damaged fuel nozzle guide from an inner portion of the fuel nozzle guide, manufacturing a replacement heat shield for the damaged fuel nozzle guide, and joining the replacement heat shield to the inner portion of the fuel nozzle guide.

A repair method for repairing an assembly including a main body and an old reinforcement, the assembly including an initial hole passing through the old reinforcement and at least a portion of the main body, the method including removing the old reinforcement; positioning a plug in the initial hole in the main body; fastening a new reinforcement on the main body, the new reinforcement covering the plug; and forming a new hole passing through the new reinforcement and at least a portion of the main body.

The present invention relates to a method for producing and/or repairing wear-stressed recesses or openings on components (22) of a turbomachine, especially of elements of a flow passage boundary, and also to corresponding components, wherein the method comprises: producing an at least two-layer molded repair part (15), one layer (2) of which is formed by an Ni-solder and a further layer (3) of which is formed from a mixture of an Ni-solder (4) and hard material particles (5) of hard alloys on a base of cobalt or nickel and which at least partially has an outer shape which is complementary to the inner shape of the recess (20) or opening which is to be repaired, inserting the molded repair part (15) into the recess (20) or opening and at least partially heat-treating the component (22) for soldering the molded repair part (15) onto the component.

A technique for repairing a dual walled component comprising a spar comprising a plurality of pedestals and a coversheet attached to the plurality of pedestals may include removing a damaged portion of the coversheet from the dual walled component to expose a plurality of exposed pedestals and define a repair location and an adjacent coversheet portion. The technique also may include filling space between the plurality of exposed pedestals with a stop material. The stop material may define a surface substantially aligned with a pedestal-contacting surface of the adjacent coversheet portion. In some examples, the method additionally includes positioning a braze material on the surface of the stop material and attaching the braze material to the plurality of exposed pedestals and adjacent coversheet portion to form a repaired coversheet portion.

Methods of manufacturing or repairing a turbine blade or vane are described. The airfoil portions of these turbine components are typically manufactured by casting in a ceramic mold, and a surface made up of the cast airfoil and at the least the ceramic core serves as a build surface for a subsequent process of additively manufacturing the tip portions. The build surface is created by removing a top portion of the airfoil and the core, or by placing an ultra-thin shim on top of the airfoil and the core. The overhang projected by the shim is subsequently removed. These methods are not limited to turbine engine applications, but can be applied to any metallic object that can benefit from casting and additive manufacturing processes. The present disclosure also relates to finished and intermediate products prepared by these methods.

A method for repairing an upstream rail of a turbine engine turbine casing, the casing including a casing body extending along a longitudinal axis, the upstream rail including: a base including a radial surface, extending substantially radially from the casing body; a plate including an upper surface, extending substantially along the longitudinal axis; and a connection portion between the base and the plate, including a concave surface connecting the radial surface and the upper surface, the concave surface and the radial surface extending on either side of an edge, the method including: covering a surface with a solder, the surface including the upper surface and the concave surface, such that the solder extends substantially until the edge; and a step of machining the covered surface, in a single action, in the direction of the radial surface, and at least until the edge, so as to reshape the surface.