The invention relates to a method for repairing an aircraft or gas turbine component, wherein the method comprises the following automated steps: a) checking the component for cracks by means of an optical measurement method, wherein determined geometry and/or damage data are stored with reference to the component, b) generating an adaptive processing strategy on the basis of the determined geometry and/or damage data in a data processing unit, c) machining the component, d) determining the changed geometry data of the component, e) performing repair welding, f) checking the component for cracks by means of an optical measurement method.

A method of making a fluid injector for a gas turbine engine includes depositing material onto a piece of tube stock. The method includes machining the deposited material into a fluid injector component. Depositing can include laser cladding the material onto the piece of tube stock. The method can include placing or flowing braze into a braze joint location between the deposited material and another fluid injector component and forming the braze into a braze joint in the braze joint location.

A method for filling cooling holes in a component of a gas turbine engine is disclosed. The component may include a plurality of first cooling holes extending through the wall of the component. The method may comprise the steps of exposing the outer surface of the component, filling the plurality of first cooling holes with a polyimide, curing the polyimide to block the passage of cooling fluid through the plurality of first cooling holes, and applying a thermal bather coating over the outer surface of the component. The method may further include the step of installing a second plurality of cooling holes in the wall of the component wherein the plurality of second cooling holes penetrate the thermal barrier coating and the wall of the component and allow cooling fluid to pass therethrough.

A circular hydraulic press reforms and resizes a chamber opening in a combustion chamber housing. The press comprises a bar having a U-shaped end and a pair of free ends. The press comprises a panel having a C-shaped edge, a mounting edge, and a pair of slotted edges. The U-shaped end of the bar and the C-shaped edge of the panel buttress the perimeter of the chamber opening. The slotted edges and a pair of tubes on the slotted edges slidably receive the free ends of the bar to enable displacement of the panel towards the bar. A disk having a predetermined annular shape and circumference positions in the chamber opening. A hydraulic piston displaces the C-shaped edge of the panel towards the U-shaped end of the bar to press the chamber opening against the disk, and thereby reform the disk to substantially the same shape and circumference as the disk.

In a method for installation of a transition duct in a gas turbine engine, a guide structure is positioned that extends in an inclined direction with respect to a gas turbine axis. At least a portion of the guide structure is disposed between a turbine section and a combustor section of the gas turbine engine. The transition duct is engaged with the guide structure such that the transition duct is movable along the guide structure. Motion is imparted to the transition duct along the guide structure in a forward-to-aft direction, to move the transition duct to an installed position in which an aft end of the transition duct is aligned for attachment to a forward face of a stator component of the turbine section.

An assembly for a turbomachine combustion chamber, including a boss for turbomachine combustion chamber, including a tubular body configured to be inserted in a receiving orifice formed in an annular wall of a flame tube and to accommodate a shank of a connecting pin for connecting the flame tube to an external casing, a first end of the boss including an annular flange configured to prevent radial translational movement of the boss in a first direction, and a second end of the boss being configured to be crimped to the wall of the flame tube so as to prevent radial translational movement of the boss in a second direction, and an annular element configured to fit coaxially with the receiving orifice and in radial contact with the annular wall of the flame tube on the one hand and with the annular flange of the boss on the other.

The present invention relates to a combustion chamber tile of a gas turbine with a plate-like basic element which is provided with at least one effusion cooling hole extending through the basic element from a surface of one side to the other side, with the effusion cooling hole being designed, from the one side of the basic element and beginning from an inlet opening, substantially at right angles to the surface over part of its length, wherein the effusion cooling hole inside the basic element has a straight section and is then provided with an offset section.

A method of reconditioning and fabricating turbine components is provided. In one embodiment, the method is performed on a fuel nozzle assembly of a gas turbine, and comprises providing a pre-assembled fuel nozzle assembly having a base, a body extending from the base to a fuel nozzle tip, an inner assembly, and an outer assembly. The method further comprises removing at least a portion of the fuel nozzle tip and the inner assembly, coupling and joining a replacement inner assembly to the base, and coupling and joining a replacement fuel nozzle tip to the replacement inner assembly and to the outer assembly to provide a reconditioned fuel nozzle.

A combustor is provided with a combustion liner (12) in which a combustion gas flows through the inner peripheral side and a plurality of through-holes (14) are formed, and a sound attenuator (20) having a space-forming member (21) configured to form a space (S) connected to the plurality of through-holes (14) at the outer peripheral side of the combustion liner (12). A method of repairing a combustor involves executing: an opening step of opening a portion of the space-forming member (21) in contact with the outside and bringing the outside and the space (S) in communication with each other; a cylinder repair step of repairing the combustion liner (12); a foreign substance removal step of removing foreign substances in the space (S) from the opening (23) opened in the opening step to the outside, after the cylinder repair step; and a closing step of closing the opening (23) using a lid (24), after the foreign substance removal step.

This disclosure describes an improved method of electron beam (EB) welding utilizing a collection pocket. The method includes providing a first surface and a second surface, forming a collection pocket in at least one of the first surface and the second surface, coupling the first surface to the second surface at a joining location, and EB welding the first surface and the second surface to each other at the joining location. The collection pocket captures and contains excess weld material to prevent the excess material from escaping the joining location, and also reduces an amount of wall thickness required for EB welding. A method of reconditioning gas turbine components is also disclosed.