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.

A hydrophilic surface pattern on a removal surface of a steam turbine directs surface moisture in at least one predetermined direction to enhance moisture management by enhancing moisture removal or otherwise reducing erosion caused by moisture in the steam turbine. In some embodiments, the removal surface is located on the outer surface of the nozzle wall adjacent an extraction opening. In some embodiments, the removal surface is located on the surface of the bucket and directs moisture toward the turbine rotor. In some embodiments, the removal surface is located on the surface of the turbine casing or the surface of the nozzle and directs moisture toward a drain in the turbine casing. The hydrophilic surface pattern is preferably laser-etched as a nano-scale pattern to create the hydrophilic surface. In some embodiments, the hydrophilic surface pattern creates a superhydrophilic surface.

A blade airfoil for an internally cooled turbine rotor blade has suction-side and pressure-side side walls, which, extending from a common leading edge to a common trailing edge and in a span direction from a root-side end to a tip-side end, at least partially enclose a cavity. The tip-side end includes a tip wall which delimits the cavity at the tip side. At least one cooling hole for the discharge of cooling fluid that can be caused to flow in the interior is provided. In the cavity, at least one rib which extends from the tip wall in the direction of the root-side end projects from the inner surface, surrounding the rib, of the suction-side side wall and/or from the inner surface of the pressure-side side wall. An inflow-side end, in relation to the cooling fluid, of the at least one cooling hole opens out laterally in the respective rib.

A method of controlling an extent of a thermal barrier coating (TBC) sheet spall and a hot gas path (HGP) component are disclosed. The method provides an HGP component having a body with an exterior surface. Controlling the extent of the TBC sheet spall includes forming a TBC over a selected portion of the exterior surface of the body. The TBC includes a plurality of segments in a cellular pattern. Each segment is defined by one or more slots in the TBC, and each segment has a predefined area such that the extent of the TBC sheet spall is limited by the predefined area of each of the plurality of segments that constitute the TBC sheet spall.

The present disclosure is directed to a rotor blade and method for forming the rotor blade. The rotor blade includes a platform having a bottom side radially spaced from a top side and a leading edge portion axially spaced from a trailing edge portion. An airfoil extends radially outwardly from the top side of the platform and a shank extends radially inwardly from the bottom side of the platform. The shank includes a lip that extends axially outwardly from a forward wall of the shank. The lip defines a radially inward surface and a radially outward surface and a plurality of slots. Swirler vane inserts are disposed within respective slots of the plurality of slots. Each swirler vane insert extends radially inwardly from the inward surface of the lip and axially outwardly from the forward wall of the shank.

A system and method for automated laser ablation includes an end effector for performing laser ablation at a location with restricted access. The systems and methods of the present disclosure specifically provide for a miniature laser end effector which may be inserted through a port or bore in order to ablate the surface of an internal component of a complex assembly. In several embodiments of the present subject matter, the end effector is mounted on an automated machine and coupled to a laser system.

A liner of a combustor wall assembly generally defines a combustion chamber and includes a film cooling circuit having a channel communicating through a hot face of a substrate of the liner. An aperture of the circuit is defined by the substrate, extends through the cold face and is in fluid communication with the channel. The hot face of the substrate is covered with a coating that extends over and thus defines in-part the channel. A film cooling hole extends through the coating and is in fluid communication with the channel. A method of manufacturing the circuit includes casting the substrate with the aperture and hole; then placing an insert into the channel prior to application of the coating over the substrate and insert. The insert is then removed and the film cooling hole is formed through the coating.

Methods for forming a hole in a coated component are provided. The method may include forming a sacrificial layer over a ceramic barrier coating of a substrate, drilling a hole into the coated component such that any spatter formed during drilling deposits onto the sacrificial layer, and removing the sacrificial layer along with the spatter deposited thereon. The sacrificial layer may include a rare earth oxide (e.g., rare earth oxide particles). Intermediate ceramic matrix composite (CMC) component are also provided. The intermediate CMC may include a CMC body, an environmental barrier coating on the bond coating, and a sacrificial layer on the environmental barrier coating, with the sacrificial layer including particles of a rare earth oxide dispersed in a polymeric matrix.

A method for treating a surface of a contoured titanium substrate used for adhesively bonded engine components. The method including applying energy from a fiber laser system to a contoured surface of a titanium substrate, the laser energy is distributed to the contoured titanium surface by at least one of direct light of sight, reflection, or scattering of one or more laser beam.

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.