A cooling jacket for a hollow airfoil of a turbine nozzle of a turbomachine, includes a main body including a central intake duct central defining a first ventilation air circulation area and connected to suction and pressure faces including at least two rows of drill holes by two separating walls defining second and third ventilation air circulation areas, an outer plate including first, second and third holes to allow the ventilation air respectively into the first, second and third ventilation air circulation areas, and an inner plate including a central opening to expel air from the first ventilation air circulation area, the outer and inner plates being secured by respectively soldering to the main body to form a one-piece unit with three ventilation air circulation areas, independent and airtight with respect to one another, before its installation in the hollow airfoil of the nozzle.

The invention relates to a method of surface marking a mechanical part with a predefined graphical representation, the method comprising using a laser source to apply a single laser pulse to an outside surface of a part for marking, with a mask being interposed between the laser source and the outside surface of the part, the mask having a predefined graphical representation, and the laser pulse having power flux density of at least 20 MW/cm.sup.2 and a duration less than or equal to 100 ns.

A component has an edge extending in a first direction. The component includes a filler disposed in the component. The filler has at least a first portion and a second portion. The first portion extends in a second direction from the edge into the component. The second portion of the filler extends from the first portion in a third direction. The second direction is substantially orthogonal to the first direction.

A conduction riser additively manufactured onto thin metal parts, the conduction riser extending in a build direction of the thin metal part and traversing the thin metal part as the conduction riser extends in the build direction. The conduction riser transferring heat from the upper layers of additively manufactured part during manufacturing, preventing thermal deflection of the part.

A manufacturing method is provided during which a substrate aperture is formed through a substrate of a preform component for a turbine engine using a first machining process. A coating system is applied onto the substrate to provide a coated substrate. A coating aperture is formed through the coating system using a second machining process that is different than the first machining process. The second machining process includes percussion laser drilling. At least the substrate aperture and the coating aperture collectively form a cooling aperture through the coated substrate.

A single-body balance correction range in which a weight has been removed by single-body balance correction performed on a turbine wheel (a rotor) as a single body is calculated, an assembly balance correction range is calculated in an assembled state of the turbine wheel, and assembly balance correction is performed in a case where the single-body balance correction range and the assembly balance correction range overlap each other, such that an outermost diameter of an arc-shaped assembly-balance correction groove provided by removal of an inner part of a turbine wheel head is smaller than a remaining height a of the single-body balance correction range.

A turbomachinery component includes an airfoil section with a cooling passage extending within the airfoil section. A wall is defined between the cooling passage and an exterior surface of the airfoil. At least one row of cooling holes is positioned along a cooling portion of the external wall proximate a leading edge of the airfoil for fluid communication between the cooling passage and the exterior surface of the airfoil. The cooling portion of the airfoil wall is thicker than an average adjacent airfoil wall thickness.

Various embodiments include a system for machining a hole in a turbine blade. The system can include: a mount for engaging a first side of a turbine rotor, the mount including: a drill plate for coupling with the first side of the turbine rotor, the drill plate having: a body; a feed opening on a first side of the body; a passage extending from the feed opening through the body; and a second opening on a second side of the body, the second opening coupled with the passage and positioned to align with the pre-formed hole in the turbine rotor; an alignment bushing for engaging the pre-formed hole in the rotor at a second side of the rotor; and a cutting device for extending through the body and alignment bushing, the cutting device for machining the hole in the blade, the cutting device aligned along a chamfer axis relative to a primary axis of the turbine rotor.

A containment structure for surrounding a rotatable machine includes a double-walled inner shell having a forward end, an aft end, and a substantially cylindrical body extending therebetween. The inner shell includes an inner wall at least partially surrounding a bladed portion of the bladed rotor, and an outer portion that branches radially outward from the inner wall. The containment structure also includes a substantially cylindrical back sheet coupled to the outer portion and disposed radially outward of the inner wall.

A core for gas turbine engine component comprises a body extending between first and second ends to define a length, and extending between first and second edges to define a width. A plurality of core extensions are formed as part of the body. The plurality of core extensions are positioned to be staggered relative to each other such that at least two adjacent core extensions are variable relative to each other in at least one dimension. A gas turbine engine component is also disclosed.