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 self-cooled orifice structure that may be for a combustor of a gas turbine engine, and may further be a dilution hole structure, includes a hot side panel, a cold side panel spaced from the hot side panel, and a continuous inner wall extending between the hot and cold side panels and defining an orifice having a centerline and communicating axially through the hot and cold side panels. A plurality of end walls of the structure are in a cooling cavity that is defined in-part by the hot and cold side panels and the inner wall. Each end wall extends between and are engaged to the hot and cold side panels and are circumferentially spaced from the next adjacent end wall. A plurality of inlet apertures extend through the cold side panel and are in fluid communication with the cavity, and each one of the plurality of inlet apertures are proximate to a first side of a respective one of the plurality of end walls. A plurality of outlet apertures extend through the hot side panel and are in fluid communication with the cavity, and each one of the plurality of outlet apertures are associated with an opposite second side of a respective one of the plurality of end walls.

In one aspect, a method for performing in situ repairs of internal components of a gas turbine engine may generally include inserting a repair tool within an interior of the gas turbine engine such that a tip end of the repair tool is positioned within the gas turbine engine and an exterior end is positioned outside the gas turbine engine. The method may also include positioning the tip end of the repair tool adjacent to a defect of an internal component, wherein the defect defines a fillable volume along a portion of the internal component. In addition, the method may include intermixing two or more constituents of a repair agent within the repair tool at a mixing location defined within the gas turbine engine, and expelling the repair agent from the tip end such that the fillable volume is at least partially filled with the repair agent.

A method of accessing a nozzle tip assembly of a gas turbine engine fuel nozzle is disclosed. The fuel nozzle has a stem and a heat shield enclosing at least part of the stem. The nozzle tip assembly is disposed within an inner cavity of the stem. The method includes forming an opening in at least the heat shield of the fuel nozzle, the opening providing access to the inner cavity of the stem via a first end thereof. The first end of the cavity is positioned opposite to a fuel nozzle exit from which fuel is conveyed from the fuel nozzle. The method includes accessing the nozzle tip assembly in the inner cavity via the opening. The method includes closing the opening after accessing the nozzle tip assembly.

An apparatus and system for assembling a combustor comprises a push bar including a first end portion that is laterally opposed from a second end portion. A first alignment block and a second alignment block are adjustably coupled to the push bar. A first threaded rod extends through the push bar proximate to the first end portion and a second threaded rod extends through the push bar proximate to the second end portion. The first alignment block and the second alignment block extend outwardly from an aft side of the push bar and are positioned between the first threaded rod and the second threaded rod. The installation tool includes a first nut and a second nut for applying axial force to the push bar.

A torch igniter for a combustor of a gas turbine engine includes an igniter body and an igniter head. The igniter body is disposed within a high-pressure case of a gas turbine engine and extends primarily along a first axis, and includes an annular wall and an outlet wall. The annular wall surrounds the first axis and defines a radial extent of a combustion chamber therewithin. The outlet wall is disposed at a downstream end of the annular wall, defines a downstream extent of the combustion chamber, and includes an outlet fluidly communicating between the combustion chamber and an interior of the combustor. The igniter head is removably attached to the igniter body at an upstream end of the annular wall, wherein the igniter head defines an upstream extent of the combustion chamber, and includes an ignition source and a fuel injector.

A method for producing a diffusion cooling hole extending between a wall having a first wall surface and a second wall surface includes forming a cooling hole inlet at the first wall surface, forming a cooling hole outlet at the second wall surface, forming a metering section downstream from the inlet and forming a multi-lobed diffusing section between the metering section and the outlet. The inlet, outlet, metering section and multi-lobed diffusing section are formed by laser drilling, particle beam machining, fluid jet guided laser machining, mechanical machining, masking and combinations thereof.

An embodiment of a combustor for a gas turbine engine includes a combustor case, a combustor liner disposed within the combustor case, a fuel nozzle at an upstream end of the combustor liner, a torch igniter at least partially within the combustor case, and a removable surface igniter. The torch igniter includes a combustion chamber, a cap configured to receive a fuel injector, a tip, an annular igniter wall extending from the cap to the tip and defining a radial extent of the combustion chamber, an aperture, a structural wall coaxial with and surrounding the igniter wall, and an outlet passage within the tip which fluidly connects the combustion chamber to the combustor. The torch igniter is configured to receive the removable surface igniter through the aperture. An internal end of the removable surface igniter extends through the aperture into the combustion chamber of the torch igniter.

Embodiments of the present disclosure generally relate to methods for cleaning aerospace components having oxidation, corrosion, contaminants, and/or other degradations. In one or more embodiments, a cleaning method includes positioning the aerospace component into a processing region of a processing chamber, introducing hydrogen gas into the processing region, maintaining the processing region at a pressure of about 100 mTorr to about 5,000 mTorr, and heating the aerospace component at a temperature of about 500° C. to about 1,200° C. for about 0.5 hours to about 24 hours to produce a cleaned surface on the aerospace component. In other embodiments, a cleaning method includes exposing the aerospace component to ozone while maintaining the aerospace component at a temperature of about 15° C. to about 500° C. for 0.25 hours to about 24 hours to produce a cleaned surface on the aerospace component.

A device for installing and removing a component in a gas turbine, includes a rail system for fastening to the gas turbine, on which rail system at least one runner is provided, which can be moved along a predetermined movement axis. A load arm is fastened to the runner, which load arm is designed to be pivoted in at least two spatial directions, and wherein the load arm has a fastening segment, which is designed to form a detachable connection to the component in question. The load arm has three joints each having a defined pivot axis, of which pivot axes preferably at least two are parallel to each other, wherein the joints each have a pivoting resistance device, which pivoting resistance devices are designed to set the pivoting resistance of the respective joints.