A process of modifying a passage in a component is provided. The process includes inserting a first material into the passage; blocking at least one end of the passage; inserting an elongated member into the passage through the first material; heat treating the passage, the first material, and the elongated member to form a solid interior in component; and machining through the solid interior to form a modified passage in the component.

A structural and/or acoustic panel including an inner skin, an outer skin, a honeycomb structure and at least one sealing flange. The sealing flange has a U-shaped section directed toward the honeycomb structure and is clamped with the honeycomb structure between the inner and the outer skins. A method for manufacturing such a panel by soldering the component elements thereof is also disclosed.

A method of applying a braze component to a honeycomb structure may comprise: applying at least a partial vacuum within a chamber, the chamber defined at least partially by a vacuum device and a cover, the honeycomb structure disposed within the chamber, the braze component disposed between the honeycomb structure and the cover; pulling the cover towards the braze component in response to applying the partial vacuum; and pulling the braze component into a plurality of hexagonal cells defined by the honeycomb structure in response to pulling the cover towards the braze component.

A turbine wheel consists of a first shroud component and a second bladed disc component. The shroud component comprises a shroud structure, a hub structure and a spoke formed integrally therewith and extending between the shroud structure and the hub structure. The bladed disc component comprises a hub member having inner and outer rims, turbine blades disposed on the outer rim, and at least one receiving zone for receiving the spoke, said at least one receiving zone extending radially between the inner and outer rims. The shroud component and the bladed disc component are connected and thus provide the turbine wheel with a shrouded portion. A shrouded turbine wheel can therefore be conveniently assembled starting from at least two components. Further, these components have simplified geometries for easy manufacture, for example using a casting technique, while the overall mechanical performance of the turbine is preserved or improved.

A method of furnace-less brazing of a substrate is provided. The method includes providing a substrate having a braze region thereon; disposing braze precursor material containing a nickel powder, an aluminum powder, and a platinum group metal powder on the braze region; and initiating an exothermic reaction of the braze precursor material such that the exothermic reaction produces a braze material that reaches a braze temperature above the solidus temperature of the braze material. A braze precursor material is also provided.

A method of repairing a piston seal assembly comprises removing worn material from a piston seal groove to generate a worked seal groove, applying a groove buildup member to the worked seal groove, and disposing a seal member proximate the groove buildup member.

A method of joining includes applying braze to a braze reservoir in a first component. A second component is engaged to the first component, wherein a joint location is defined between the first and second components. A wicking structure provides flow communication from the braze reservoir to the joint location. The method also includes joining the first and second components together at the joint location by applying heat to the braze to flow the braze from the reservoir through the wicking structure to the joint location to form a braze joint at the joint location.

A hybrid diffusion-brazing process and hybrid diffusion-brazed article are disclosed. The hybrid diffusion-brazing process includes providing a component having a temperature-tolerant region and a temperature-sensitive region, brazing a braze material to the temperature-tolerant region during a localized brazing cycle, then heating the component in a furnace during a diffusion cycle. The brazing and the heating diffusion-braze the braze material to the component, and the localized brazing cycle is performed independent of the diffusion cycle in the hybrid diffusion-brazing process. The hybrid diffusion-brazed article includes a component, and a braze material diffusion-brazed to the component with a filler material. The filler material has a melting temperature that is above a tolerance temperature of the component.

A method of manufacturing a hollow aerofoil component 100 for a gas turbine engine 10 comprises joining a first panel 200 to a second panel 300 using bonding, and hot forming the panels into shape. The bonding step and the hot forming step are performed in the same rig, thereby optimizing process time and component quality.

A stiffness boss for a turbine case of a gas turbine engine is disclosed. The stiffness boss includes a head portion disposed on an outer case surface of the turbine case, the head portion configured to provide rigidity in response to a transverse load being applied to the turbine case in a transverse direction. The stiffness boss also includes a leg portion disposed on the outer case surface of the turbine case and connected to the head portion, the leg portion configured to provide rigidity in response to an axial load being applied to the turbine case in an axial direction, such that deformation of the turbine case is resisted.