B23P6/04

Apparatus and method for treating rotatable component

Embodiments of the present disclosure relate generally to an apparatus and method for treating a rotatable component. An apparatus according to the present disclosure can include: a sliding engagement member configured to slidably engage a portion of a rotating component that is temporarily stationary; and a tool engaging member for positioning a machining tool relative to the rotating component to machine a surface of the rotating component, wherein the tool engaging member is rotatable to one of a plurality of angles relative to the sliding engagement member.

REPAIR OF AN ASSEMBLY COMPRISING A MAIN BODY AND A REINFORCEMENT

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.

REPAIR OF AN ASSEMBLY COMPRISING A MAIN BODY AND A REINFORCEMENT

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.

DIRECTED ENERGY DEPOSITION FOR PROCESSING GAS TURBINE ENGINE COMPONENTS

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.

REPAIR MATERIAL PREFORM

A structural element for repairing a damaged component comprising a shaped cavity configured to receive the damaged component and a repair material, the shaped cavity comprising a material having a first melting point and the repair material comprising a material having a second melting point that is lower than the first melting point. The shaped cavity may comprise a preform for the damaged component. The preform may comprise a mold configured to reconstruct the shape of the damaged component. The repair material may comprise a first material and a second material, the second material having a melting point that is lower than the first material. The repair material may comprise a Nickel-Boron composition. The repair material may have a melting point that is approximately 40 degrees Fahrenheit lower than the melting point of the damaged component.

System and Method for In Situ Repair of Gas Turbine Engine Casing Clearance
20170239762 · 2017-08-24 ·

The present disclosure is directed to a system and method for repairing an abradable material coated on a casing of a gas turbine engine. The system includes an articulating guide configured to fit into an access port of the gas turbine engine. Further, the articulating guide has a proximal end and a distal end. The system also includes a repair tool configured at a distal end of the articulating guide. The repair tool includes a body having a proximal end and a shaped distal end, with the shaped distal end extending away from the body. Thus, the shaped distal body is configured to trench out an area of the abradable material comprising a defect. The system also includes a filler material for filling the trenched out area.

Mobile pipe resurfacing and inspection rack
11426827 · 2022-08-30 ·

A mobile pipe rack workstation for inspecting and repairing pipe materials, a “Pipe Station.” By folding the pipe station's load/unload arms, removing any tool's from the tool mount and lowering the gantry by retracting the risers; the pipe station is transportable on public roadways without permitting, escorting, or special signage required for oversized loads.

Mobile pipe resurfacing and inspection rack
11426827 · 2022-08-30 ·

A mobile pipe rack workstation for inspecting and repairing pipe materials, a “Pipe Station.” By folding the pipe station's load/unload arms, removing any tool's from the tool mount and lowering the gantry by retracting the risers; the pipe station is transportable on public roadways without permitting, escorting, or special signage required for oversized loads.

SYSTEM AND METHOD FOR SERVICING A JOINTED ROTOR BLADE OF A WIND TURBINE
20220268262 · 2022-08-25 ·

A method is provided for servicing a jointed rotor blade of a wind turbine. The jointed rotor blade is positioned in a six o'clock position and a blade tip support element is secured to a tip section of the jointed rotor blade. A lift-support element is secured at a mounting location above the blade tip support element. A lifting line is coupled between the lift-support element and the blade tip support element. The tip section is separated from the root section of the jointed rotor blade such that the tip section is suspended above a support surface of the wind turbine via the blade tip support element and the lifting line. The tip section of the jointed rotor blade is serviced.

In Situ Gas Turbine Prevention of Crack Growth Progression

A method for remotely stopping a crack in a component of a gas turbine engine is provided. The method can include inserting an integrated repair interface attached to a cable delivery system within a gas turbine engine; positioning the tip adjacent to a defect within a surface of the component; temporarily attaching the tip adjacent to the defect within the surface on the component; supplying a new material to the area to fill the defect; and heating the new material to fuse the new material to the component within the defect.