In the method for carrying out work, according to the invention, in order to maintain a metal turbine engine motor, such as a drum, in an operational state: an upstream and/or downstream face (343) of a circumferential groove (34) of the rotor is ground, with said face having recessed marks that the grinding is intended to remove or at least blur, and foils (43) are placed in the groove between the blades of the rotor (24) and the rotor, at least in the area where the face has been ground.

The invention relates to an exhaust turbocharger, which contains a modular bearing, which is designed for bearing a shaft and is arranged between a compressor and a turbine, wherein the bearing has a bearing housing having a receptacle chamber, wherein a bearing assembly module can be or is installed in the receptacle chamber and can be non-destructively removed, the receptacle chamber being sized such that optionally either a bearing assembly module having a rolling bearing or a bearing assembly module having a slide bearing can be installed, the receptacle chamber having an interface, which is designed to contact the bearing flange of a bearing assembly module inserted into the receptacle chamber, the interface being designed to connect an oil gallery passing through the bearing housing to one or more oil galleries passing through a bearing flange of the bearing assembly module.

The present disclosure is directed to an improved system and method for repairing a bend in a turbine blade of a turbine of a gas turbine engine. The system includes an articulating guide configured to fit into an access port of the turbine. The articulating guide includes a proximal end and a distal end. The system also includes a repair tool configured at the distal end of the articulating guide. Further, the repair tool is configured to fit over the turbine blade. Thus, the repair tool is configured to bend the turbine blade to an unbent position while the turbine blade is secured within the turbine.

Disclosed is a repair method for guide blades of a gas turbine. The method comprises: providing at least one guide blade to be maintained; capturing the actual geometry of the guide blade to be maintained with application of at least one measuring method; comparing the actual geometry captured by the contactless measuring method to a predetermined desired geometry for a corresponding guide blade type; calculating a target geometry for the guide blade to be maintained, which corresponds as much as possible to the desired geometry, such that using optimization parameters, the desired geometry of the guide blade to be maintained is approximated at least in sections along its flow contour; applying material and removing material by machine on the guide blade, such that the calculated target geometry is produced.

Methods for material build-up on a tip of a blade of a gas turbine engine are provided. The method can include inserting a material supply adjacent to the tip and directing a laser onto the interface of the material supply and the tip such that the material supply melts and attaches to the tip. Methods are also provided for remotely stopping a crack in a component of a gas turbine engine. 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; supplying a new material to the fillable area to fill the defect; and directing a laser to the new material within the fillable area to fuse the new material to the component within the defect.

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.

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 defined on a surface on the component; and locally heating the base of the defect. A method is also provided for clamping a crack defined between a first surface and a second surface of a component of a gas turbine engine. The method can include attaching a strap over the crack such that a first end of the strap is attached to the first surface of the component and the second end of the strap is attached to the second surface of the component.

Methods for remotely joining material a surface area of a component of a gas turbine engine are provided. The method can include inserting an integrated repair interface attached to a cable delivery system within a gas turbine engine; positioning a tip of the integrated repair interface adjacent to a defect defined within a surface of the component; temporarily attaching the tip adjacent to the defect within the surface of the component; and supplying a new material to the area to fill the defect.

Methods provided for remotely stopping a crack in a component of a gas turbine engine are provided, along with methods of remotely cleaning a surface area of a component of a gas turbine engine. 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; and drilling a hole into the base of the defect. An integrated repair interface is also provided.

This invention relates to the repair and removal of erosion or impact damage with a liquid repair material using a flexible applicator capable of conforming to the surface of the leading edge of the airfoil while being drawn lengthwise along the airfoil surface of a helicopter or wind turbine rotor blade thereby restoring the aerodynamic contour with or without the addition of an optional topcoat layer.