A tool for balancing a turbine engine module in a balancer, the module including a stator, a rotor and a shaft, the balancer including at least one power drive unit and a table equipped with two support of the shaft of the module. The tool includes at least: one stator support, fixed on the table of the balancer behind the supports, a tubular false bearing, configured to support a bearing for guiding the rotor in the stator and protruding outside of the stator, a guiding sleeve of the shaft, confining a support of the false bearing, and received on the supports of the balancer, a rear support plate of the stator, fixed to the support of the stator, and immobilising the rotor with respect to the stator, a front support plate of the stator, fixed to the stator support, and immobilising and centring the false bearing.

A method for closing a plurality of holes penetrating from a first surface of a metal article through a second surface of the metal article is disclosed including applying the metal composition to the first surface along a bridging application path. The bridging application path passes over the plurality of holes between a first edge of each of the plurality of holes and a second edge of each of the plurality of holes. Applying the metal composition along the bridging application path closes the plurality of holes.

A service apparatus for use in maintaining a turbine assembly (100) includes a carriage (132, 304) configured to move through a cavity of the turbine assembly (100), a motorized system (218, 500, 600, 700, 800) coupled to the carriage (132, 304), and a maintenance device (128, 400) coupled to the motorized system (218, 500, 600, 700, 800). The motorized system (218, 500, 600, 700, 800) is configured to move the maintenance device (128, 400) relative to the carriage (132, 304). The motorized system (218, 500, 600, 700, 800) includes a first motor (710, 720, 805) configured to move the maintenance device (128, 400) in a first direction (324) and a second motor (710, 720, 805) configured to move the maintenance device (128, 400) in a second direction (324).

In some embodiments, a process treats a turbine component. The turbine component includes an article and a wear component brazed to the article. The process includes applying a braze tape on at least a portion of the wear component and thermal processing the turbine component while the braze tape is on the at least a portion of the wear component to treat the turbine component. In some embodiments, an assembly includes a turbine component. The turbine component includes an article and a pre-sintered preform brazed to a surface of the article. The assembly also includes a braze tape on at least a portion of the pre-sintered preform. In some embodiments, a treated turbine component includes a treated article and a pre-sintered preform brazed to a surface of the treated article. The treated turbine component has been thermally processed with the pre-sintered preform being substantially free of re-flow.

Provided is a turbine blade of a gas turbine including a turbine blade part having an airfoil shape including an internal cavity therein, a cast tip disposed at an upper portion of the turbine blade part, and a braze joint to attach the turbine blade part and the cast tip to each other. The turbine blade part and the cast tip has substantially the same cross-sectional shape in a top plan view. In addition, the turbine blade part further includes a protrusion disposed at a surface where the turbine blade part is attached to the cast tip. In a similar manner, the cast tip may have a concave portion at a surface where the cast tip is attached to the turbine blade part to allow the concave portion to be coupled to the protrusion of the turbine blade part.

The method comprises the steps of: a) cutting the shaft of the rotor at a section plane perpendicular to the axis of rotation of the shaft so as to separate the end portion of the shaft on which the bladed discs to be replaced are mounted from the remaining portion of the shaft; b) providing, for each bladed disc to be replaced, a corresponding new bladed disc with a respective hub having a solid cross-section; c) providing a new end portion of the shaft with a solid cross-section; and d) clamping the new bladed discs between the remaining portion of the shaft and the new end portion of the shaft, securing them to the remaining portion of the shaft by anchor bolts.

A method for working an airfoil cluster is disclosed. The method may include attaching a first datum to a first portion of the airfoil cluster, and joining a second portion of the airfoil cluster to the first portion, the second portion having a second datum substantially aligned with the first datum in a common plane spaced away from the first and second portions.

Provided is a method for maintaining an axial-flow turbomachine, which has a support structure and a plurality of axially adjacent guide vane rings each of which has a plurality of guide vanes, each guide vane having at least one platform, the platforms being fastened to the support structure by means of retaining elements, wherein facing platform end faces of axially adjacent guide vanes define sealing sections made of a metal material, the sealing sections being associated with each other and jointly forming a sealing assembly.

A method of remanufacturing a turbine component is provided. This method includes removing a donor portion from a damaged component; removing a to-be-replaced portion from a serviceable component generally equivalent to the donor portion leaving a remainder; and welding the donor portion to the remainder. A BOAS for a gas turbine engine is also provided that includes a serviceable BOAS with a donor portion from a damaged BOAS welded thereto.

A pre-sintered preform (114) and a repair process (100) utilizing the pre-sintered preform (114) are disclosed, each of which result in a brazement (116) comprising a replacement protective coating (118) deposited on a component surface (110). The protective coating (118) exhibits excellent temperature and oxidation resistance, improved adhesion to superalloy surfaces, and reduced depletion over a service life of the associated component (102).