A tuned mass damper for reducing vibration on a component includes a shaft connector member configured to be coupled to the component and a cable termination member. The tuned mass damper also includes at least one cable coupled to the shaft connector member and to the cable termination member such that vibration of the component is transferred to the at least one cable via the shaft connector member and increased or decreased by the at least one cable.

A method comprising applying braze to a joint location of two work pieces and applying local heating to the joint location of the two work pieces until braze melting temperature is achieved to melt the braze while maintaining temperature of more remote portions of each work piece. The method includes reducing heating of the braze to form a braze joint joining the joint location of the two work pieces.

A method includes joining a fuel plurality of injection components to a fuel manifold, wherein for each fuel injection component in the plurality of fuel injection components, a metallic joint is formed joining and sealing the fuel injection component to the manifold. A system includes a fuel manifold. A plurality of fuel injection components are connected in fluid communication with the fuel manifold with metallic joints sealing between each of the plurality of fuel injection components and the fuel manifold to prevent leakage from between the manifold and the plurality of fuel injection components.

The invention relates to a method for repairing a damaged blade tip of a turbine blade which is armor-plated and provided with a blade coating, of a thermal gas turbine. The method according to the invention comprises the steps of removing a blade tip armor plating of the turbine blade at least in the region of the damaged blade tip and producing a repair surface (12), removing only a part of the blade coating of the turbine blade in the region of the repair surface while preserving a part of the blade coating separated from the repair surface (14), restoring the blade tip reinforcement (20), and restoring the blade coating in the region of the repaired blade tip (22). The invention furthermore relates to a device for carrying out such a method.

A method for selectively adhering braze powders to a surface comprises applying a braze powder to a surface, and then directing a laser beam onto the braze powder while the laser beam moves along a predetermined path relative to the surface. The laser beam selectively heats the braze powder along the predetermined path such that the braze powder is sintered and bonded to the surface. Thus, a braze deposit is formed at one or more predetermined locations on the surface. After forming the braze deposit, excess braze powder, that is, the braze powder not selectively heated by the laser, is removed from the surface.

A method for forming a component for a gas turbine engine may include forming a first portion of the component that includes a cast metal or metal alloy, forming a second portion of the component that includes presintered preform defining at least one support structure, positioning the second portion on the first portion to define an assembly such that the first portion and the second portion define at least one cooling channel therebetween, and heating the assembly to join the first portion and the second portion and form the component.

Additive manufacturing techniques are used to achieve customized preforms for repair or manufacture of turbomachinery. A method of modifying a section of a product includes forming, a preform set to fit the section. A base material is selected with properties desired for the modification of the section. A binder is selected that vaporizes at a temperature below a melting point of the base material. The preform set is built by the selective application of the binder to the base material to achieve design dimensions of the section when the preform is joined to the section. The section is prepared for effecting the extent of modification and the preform is positioned on the section. The section and the preform are heated to substantially eliminate the binder from the preform and then thermally processed to harden the preform and to bond the preform to the section.

A system includes a gas turbine component having a recessed portion with a recessed surface in a hard-to-weld (HTW) material. The system includes a plate disposed over the recessed portion. The plate has an easy-to-weld (ETW) material. The plate has an outer surface and an inner surface, and the inner surface faces the recessed portion. The system includes a braze material disposed within the recessed portion between the recessed surface and the inner surface of the plate. The braze material is configured to bond the recessed surface of the recessed portion with the inner surface of the plate when the braze material is heated to a brazing temperature. The system includes a filler material disposed on the outer surface of the plate disposed over the recessed portion. Application of the filler material to the outer surface of the plate is configured to heat the braze material to the brazing temperature.

A method of manufacturing a hard-to-weld material by a beam-assisted additive manufacturing process is presented. The method includes depositing a first layer for the material onto the substrate, the first layer including a major fraction of a base material for the component and a minor fraction of a solder, depositing a second layer of the base material for the component and a thermal treatment of the layer arrangement. The thermal treatment includes a first thermal cycle at a first temperature above 1200° C. for a duration of more than 3 hours, a subsequent second thermal cycle at a second temperature above 1000° C. for more than 2 hours, and a subsequent third thermal cycle and a third temperature above 700° C. for more than 12 hours. A manufactured component is also presented.

A closed impeller includes an impeller body including a plurality of blade portions, and a shroud fitted on the impeller body. The shroud is press formed into a curved shape along end portions of the blade portions. The shroud includes a plurality of protrusions protruding from a surface facing the impeller body and extending, and curved, along the end portions of the plurality of blade portions. An amount of protrusion of each of the protrusions is less than a thickness of the shroud. A brazing material is provided at least on end portions of the protrusions.