A method of servicing a gas turbine engine, the method including preparing the gas turbine engine for service; installing a shaft protection cover to an aft end of a fan shaft of the gas turbine engine; installing an oil collector drum at least partially around a gearbox of the gas turbine engine; and removing at least a portion of the gearbox from the gas turbine engine.

An assembly for forming a gas turbine engine according to an example of the present disclosure includes, among other things, a layup tool including a main body extending along a longitudinal axis and a flange extending radially from the main body, the flange defining an edge face slopes towards the main body to an axial face. At least one compression tool has a tool body having a first tool section and a second tool section extending transversely from the first tool section. The first tool section is translatable along a retention member in a first direction substantially perpendicular to the edge face such that relative movement causes the second tool section to apply a first compressive force on a composite article trapped between the axial face of the flange and the second tool section. A method of forming a gas turbine engine component is also disclosed.

Methods and tools for facilitating the installation and/or removal of a rotor on a shaft of a gas turbine engine are provided. The tool includes a stabilizer attachable to the shaft and including a first guide counterpart. The tool also includes a holder attachable to the rotor and including a second guide counterpart for engagement with the first guide counterpart of the stabilizer. Engagement of the first and second guide counterparts guides movement of the holder relative to the stabilizer along a guide axis and prevents movement of the holder relative to the stabilizer transverse to the guide axis.

A tooling assembly for mounting a plurality of components, such as compressor blades, in a powder bed additive manufacturing machine to facilitate a repair process is provided. The tooling assembly includes component fixtures configured for receiving each of the compressor blades, a mounting plate for receiving the component fixtures, and a magnet assembly operably coupling the component fixtures to the mounting plate in a desired position and orientation to facilitate an improved printing process.

A system for automatically measuring an exhaust area of a turbine guide vane, including a data acquisition module configured to measure a three-dimensional point cloud coordinate of a contour of a throat; a positioning module configured to automatically adjust a relative spatial position between the data acquisition module and the turbine guide vane; and a data processing module configured to fit a three-dimensional contour of the throat according to the three-dimensional point cloud coordinate measured by the data acquisition module. A method for automatically measuring an exhaust area of a turbine guide vane using the system is also provided.

The present invention relates to a method for characterizing a coating, in which method a mass and/or a volume of a basic body is/are measured prior to coating; a mass and a volume of the basic body with the applied coating are measured; for characterizing the coating, a density of the coating is determined from the volume and mass measurements; wherein the volume is optically measured.

A hoist for lifting at least a portion of a gas engine assembly includes a support member including an upper portion, a lower portion, and a connecting portion extending therebetween. The hoist also includes an elongate member coupled to the lower portion of the support member and extending substantially orthogonally to the lower portion, and at least one bracket slidably engaged with the elongate member and axially translatable along a length of the elongate member. In addition, the hoist includes a plurality of linkage members coupled to the at least one bracket, where each linkage member of the plurality of linkage members is configured to attach to at least a portion of the gas engine assembly.

A method and system temporarily holds a workpiece, most suitably an aero engine turbine blade element during manufacture. The workholding system includes a support body with a contoured body surface, complementary to a workpiece surface, formed of a transparent material to define a bonding zone. The support body is supported by a base to form a workpiece shuttle, and a bond station receives the workpiece shuttle. Complementary zero-point locating elements on the shuttle and station assure accurate positioning. The bond station further has workpiece locating elements configured to accurately position the workpiece on the shuttle in a predetermined position relative to the zero-point locating elements of the shuttle, thereby compensating for shuttle-to-shuttle variance. An adhesive, such as a UV curable adhesive, is applied to the bonding zone and cured by UV through the transparent material, thereby fixing the workpiece in the predetermined position.

A maintenance method for a steam turbine including a rotor, a casing for accommodating the rotor, and a bearing box for accommodating a bearing which supports the rotor includes: a step of installing an expansion-and-contraction member below the rotor by using an upward facing flat surface disposed between the casing and the bearing box in an axial direction; and a step of pushing up the rotor upward by the expansion-and-contraction member.

A method of evaluating compliance of a component of an aircraft engine with flow requirements has: obtaining experimental data from experimental testing on a prototype of the component; obtaining a digitized model of a production model of the component, the digitized model including digitized apertures having geometrical data corresponding to that of apertures defined in the production model; computing a nominal mass flow rate through the digitized apertures using the geometrical data and flow parameters from the experimental data; correcting the nominal mass flow rate of the digitized model to obtain a computed mass flow rate of the production model; and assigning at least one parameter to the production model, the at least one parameter indicative of installation approval of the production model of the component for installation on the aircraft engine when the computed mass flow rate is determined to be within a prescribed range of the flow requirements.