A manufacturing method is provided during which a preform component for a turbine engine is provided. A cooling aperture is formed in the preform component. The cooling aperture includes a centerline, an inlet and an outlet. The cooling aperture extends longitudinally along the centerline through a wall of the preform component from the inlet to the outlet. The forming of the cooling aperture includes forming a first portion of the cooling aperture using a machining tool implement with a first toolpath that is angularly offset from the centerline by a first angle between thirty-five degrees and ninety degrees.

A combustor component according to at least one embodiment of the present invention includes a cylindrical body which internally includes a combustion chamber, and includes a weld part where a plurality of through holes opening to the combustion chamber are formed, and a housing which is disposed on an outer circumferential side of the cylindrical body to cover a part of the weld part, and defines an acoustic damping space communicating with the combustion chamber via at least one of the through holes. The plurality of through holes in the weld part has a formation density which is higher in a first region of the weld part covered with the housing than in a second region of the weld part positioned outside the housing.

An environmental barrier coating, comprising a substrate containing silicon; an environmental barrier layer applied to said substrate; said environmental barrier layer comprising a rare earth composition.

Wall assemblies for a combustor of a gas turbine engine are disclosed. A wall assembly comprises an outer shell made of a metallic material, adjacent first and second inner panels mounted to the outer shell via an insert and a damper disposed between the outer shell and at least one of the first and second inner panels. The first and second inner panels may be spaced apart from the outer shell to define a double-wall configuration with the outer shell. The first and second inner panels may be made of a composite material. The insert may be made from substantially the same or other type of composite material.

A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a forward liner segment; an aft liner segment disposed downstream from the forward liner segment relative to a direction of flow through the combustor, the forward and aft liner segments at least partially defining a combustion chamber; and an intermediate member disposed at least partially between the forward and aft liner segments and extending in the circumferential direction.

A micro-turbine core fabricated as a single part using 3D additive manufacturing (AM) to simultaneously form sequential layers of at least two static components from any of the following static components: central bearing support structure, outer casing, combustor complete, nozzle guide vanes (NGVs), diffuser, diffuser outer casing, fuel manifold, fuel injector(s), igniter mounting boss, oil manifold, oil distribution lines, or turbine outer casing. The single part does not require fastening hardware, welding, and/or bonding processes to create the single part.

[Problem] To provide a fuel nozzle for a gas turbine combustor, offering favorable durability and strength reliability. [Solving Means] A method for manufacturing a fuel nozzle for a gas turbine combustor, the method comprising: (a) fitting a fuel nozzle having an internal through hole into a through hole or a recess provided in a base plate; (b) bonding, by a fusion joint or a brazing joint, the fuel nozzle to the base plate in an interface therebetween on a surface of the base plate; and (c) following the step of (b), subjecting the fuel nozzle and the base plate to a pressure bonding process to thereby pressure bond the fuel nozzle and the base plate in the interface therebetween.

By melting a shaping material in which a metal powder and a binder are mixed and by carrying out injection molding (primary shaping) in an injection mold, an injection molded body, or an intermediate shaped body are produced. The injection molded body or the intermediate shaped body is placed by a transfer mold and is subjected to a gravity shaping (secondary shaping) with a transformation. A sintered body is manufactured by carrying out debindering and sintering to the injection molded body.

An automated preparation method of a SiC.sub.f/SiC composite flame tube, comprising the following steps: preparing an interface layer for a SiC fiber by a chemical vapor infiltration process, and obtaining the SiC fiber with a continuous interface layer; laying a unidirectional tape on the SiC fiber with the continuous interface layer and winding the SiC fiber with the continuous interface layer to form and obtaining a preform of a net size molding according to a fiber volume and a fiber orientation obtained in a simulation calculation; and adopting a reactive melt infiltration process and the chemical vapor infiltration process successively for a densification and obtaining a high-density SiC.sub.f/SiC composite flame tube in a full intelligent way. The SiC.sub.f/SiC composite flame tube prepared by the present disclosure not only has a high temperature resistance, but also has a low thermal expansion coefficient, high thermal conductivity and high thermal shock resistance.

A coating occlusion resistant effusion cooling hole to form a film of a cooling fluid on a surface of a wall. The cooling hole extends along a longitudinal axis. The cooling hole includes an inlet section defined so as to be spaced apart from the surface. The inlet section is to receive the cooling fluid. The cooling hole includes a metering section fluidly coupled downstream of the inlet section. The cooling hole includes an outlet section fluidly coupled downstream of the metering section. The outlet section includes an overhang portion, a recessed portion, a first sidewall and a second sidewall. The first sidewall and the second sidewall interconnect the overhang portion with the recessed portion along a portion of the outlet section, and the first sidewall and the second sidewall converge and diverge in a plane transverse to the longitudinal axis.