An apparatus for removing or installing a turbine blade from a turbine of a turbomachine is disclosed. The apparatus can include: an operative head configured to engage an axial sidewall of a turbine blade base. An actuator is configured to move the operative head to selectively engage the axial sidewall of the turbine blade base and impart an axial force against the turbine blade base to remove or install the turbine blade. A support gantry is configured to position the actuator substantially vertically above the turbine blade in position in the turbomachine. Among other advantages, the support gantry allows adjustment of the apparatus for different turbines, and use of the head on more than one stage of any given turbine.

A turbomachine diaphragm including a sealing section having a first end portion that extends to a second end portion through an intermediate portion; and at least one rail member including a first end section that extends from the first end portion of the sealing section to a second end section through an intermediate section having an inner surface section and an outer surface section, the second end section including multiple weld passes disposed on opposed sides of the second end section for mitigation of thermal tensions on the diaphragm, the multiple weld passes forming a cladding welded to the diaphragm, wherein the cladding includes a stainless austenitic steel.

The invention relates to a method for pickling a turbomachine component (1), comprising the following steps: positioning the component in a closed chamber (2), injecting a gas mixture (3) into the chamber (2), the gas mixture (3) comprising a halogenated gas, heating the chamber (2), the method being characterised in that: the gas mixture further comprises dihydrogen, the heating step is carried out at a temperature higher than 1000° C. and the step of injecting the gas mixture (3) is carried out by circulating through the chamber (2) a flow of gas mixture (3) having a flow rate between 6 and 15 times the volume of the chamber (2) per hour.

A method of repairing a superalloy component includes a series of sequential steps. The steps are, cleaning the component, applying brazing material to the component, heat treating the component, inspecting the component, preparing the surface of the component, welding the component, and performing a second inspection of the component. The superalloy component is comprised of a high gamma prime superalloy.

Methods of repairing a part having a firtree-shaped feature requiring rework are disclosed. An embodiment of the method includes receiving the part having the firtree-shaped feature requiring rework. The part is installed in a machine configured for wire electrical discharge machining (EDM). A location of the firtree-shaped feature relative to a datum of the machine is then determined. Wire EDM is performed on the firtree-shaped feature.

A rotor balancing method for a gas turbine having a rotor with a first correction plane and a second correction plane, wherein a first balancing weight is attached to the first correction plane. The method includes performing a first influence run wherein first balancing weight remains fitted for the subsequent second influence run; fitting a first calibration weight to the second correction plane using a reference influence vector; performing a second influence run; removing the first calibration weight from the rotor and calculating an influence vector of the second correction plane using a first set of vibration measurements and a second set of vibration measurements taken during the first influence run and the second influence run, respectively; and carrying out balancing of the rotor by fitting a final balancing weight to the first correction plane and a second balancing weight to the second correction plane using the calculated influence vectors.

A method of forming a build in a powder bed includes providing a first diode laser fiber array and a second diode laser fiber array, emitting a plurality of laser beams from selected fibers of the second diode laser fiber array onto the powder bed, corresponding to a pattern of a layer of the build, simultaneously melting powder in the powder bed corresponding to the pattern of the layer of the build, scanning a first diode laser fiber array along an outer boundary of the powder bed and emitting a plurality of laser beams from selected fibers of the first diode laser fiber array and simultaneously melting powder in the powder bed corresponding to the outer boundary of the layer of the build to contour the layer of the build. An apparatus for forming a build in a powder bed including a first diode laser fiber array and a second diode laser fiber array is also disclosed. The first diode laser fiber array configured to contour the layer of the build.

A blade repair apparatus is provided and includes a deposition head which is movable relative to base materials and configured to execute a repair operation that includes a deposition of additional materials onto the base materials during deposition head movements, a temperature control system including a temperature regulating assembly coupled with the deposition head in a trailing position and a controller. The controller is operably coupled to the deposition head and the temperature control system. The controller is configured to control the deposition head movements and depositional operations of the deposition head. The controller is configured to control the temperature control system such that the temperature regulating assembly controls temperatures of at least the base materials and the additional materials during at least the deposition head movements and the depositional operations.

A gas turbine engine component includes a gas turbine engine component body formed of a ceramic matrix composite material having at least one fastener integrally formed with the gas turbine engine component body as a single-piece structure. The gas turbine engine component body initially comprises a rigidized preform structure formed from a polymer based material. The at least one fastener connects the gas turbine engine component body to an engine support structure.

A gas turbine engine component includes a gas turbine engine component body formed of a ceramic matrix composite material having at least one fastener integrally formed with the gas turbine engine component body as a single-piece structure. The gas turbine engine component body initially comprises a rigidized preform structure formed from a polymer based material. The at least one fastener connects the gas turbine engine component body to an engine support structure.