A method for manufacturing a planet gear or a sun gear of a gearbox of a wind turbine includes forming a base of the planet gear via at least one of casting or forging. The base of the planet gear includes an inner circumferential surface and an outer circumferential surface. Therefore, at least one of the inner circumferential surface or the outer circumferential surface of the planet gear includes a plurality of net or near-net gear teeth. The method also includes applying a coating material to at least a portion of the base of the gear and at least a portion of the plurality of gear teeth of the gear via an additive manufacturing process so as to increase a hardness of the portions of the base and the plurality of gear teeth that includes the coating material.

A turbine blade has an attachment root and an airfoil. A cooling passageway system has a plurality of trunks extending from respective inlets along the root inner diameter end from a leading trunk near a first axial end to a trailing trunk near a second axial end; and a plurality of outlets along the airfoil including trailing edge outlets fed by the trailing trunk. Viewed normal to a root end-to-end centerplane: the trailing trunk has a turn passing forward and then rearward; an outside of the turn protrudes forward; and the outside of the turn has a tighter curvature than an inside of the turn.

A turbomachine housing, in particular of a radial turbomachine which transfers technical work to a process fluid or from a process fluid, includes: an opening extending along an axis, for the axial feed-through of a shaft extending along said axis; a contact surface extending along a circumferential direction with respect to the axis, for contact with a housing jacket of the turbomachine housing. A flow line provided as an inflow or outflow of the process fluid is designed as an integral part of the cover.

A cylinder head assembly for an internal combustion engine includes a cast cylinder head having at least one oil gallery, a turbocharger housing integrally cast with the cylinder head, and a turbocharger cartridge assembly configured to be inserted into the turbocharger housing and including at least one bearing rotatably supporting a shaft coupled between a compressor wheel and a turbine wheel. A lubricant passage is formed within the turbocharger housing and configured to supply oil from the at least one oil gallery to the turbocharger cartridge assembly to lubricate the at least one bearing. A seal assembly is disposed at least partially within the turbocharger housing to receive lubricant from the lubricant passage and includes a sealing end configured to seal against the turbocharger cartridge assembly.

A method for manufacturing an aeronautical part utilizes injection molding. After injecting the prepared mixtures to obtain two green blanks, an assembly area of at least one of these two blanks is heated. The blanks are assembled and then debinding is carried out. A sintering treatment is then carried out.

Methods for manufacturing combustor panels of gas turbine engines and combustor panels are described. The methods include defining a particle deposit near-steady state for at least a portion of a combustor panel, the particle deposit near-steady state representative of a build-up of particles on the at least a portion of the combustor panel during use, generating a template based on the defined particle deposit near-steady state, wherein the template includes one or more augmentation elements based on the representative of build-up of particles, and forming a combustor panel based on the template, wherein the formed combustor panel includes one or more augmentation elements defined in the template.

A core for the foundry of an aeronautical part such as a turbine blade, the core being intended to be disposed in an inner housing defined by a mold, the core comprising a body intended to form the internal shape of the turbine blade, an impact portion, disposed on at least a portion of the periphery of the body so as to break a fluid jet when filling the inner housing with the fluid, the impact portion comprising a top and at least one deflection wall converging towards the top.

A method of assembling a part is provided and includes forming a first section of the part, defining, in the first section, passages with dimensions as small as 0.005 inches (0.127 mm), forming a second section of the part, metallurgically bonding the first and second sections whereby the passages are delimited by the first and second sections and executing the metallurgically bonding without modifying a condition of the passages.

A method of repair of a part is provided and includes removing a section that is damaged from the part, casting a replacement section for the part, the replacement section having a geometry similar to that of the section in an undamaged condition and bonding the replacement section to the part using field assisted sintering technology (FAST).

An airfoil includes a platform and an airfoil section that extends from the platform. The airfoil defines leading and trailing ends and suction and pressure sides. The airfoil section has a transition region through which the airfoil section blends into the platform. The trailing end of the airfoil section has an axial cooling slot opening through the transition region and defines a circumferentially diverging ramp in the transition region.