The invention relates to a method for handling a rectifier of a turbojet of an aircraft, the rectifier having an axis defining the asymmetry thereof, said method comprising a step of placing the rectifier on the rollers of a supporting structure, the structure and the rollers thereof being arranged such that the axis of the rectifier is inclined at a non-null acute angle in relation to the horizontal, and a step of controlling, maintaining, assembling, handling, storing, deburring and/or cleaning the rectifier, during which the rectifier is pivoted about the axis thereof. The invention also relates to a trolley for handling a rectifier for an axial turbojet, said trolley comprising at least two of the lower rollers that have axes inclined in relation to the horizontal of said angle and at least one upper roller, the axis of which is inclined in relation to the vertical of said angle.

A gas turbine module includes a gas turbine that has a gas turbine rotor and a turbine shell; an inlet plenum that is connected to an inlet of the gas turbine; an exhaust plenum that is connected to an exhaust of the gas turbine; an enclosure that covers the gas turbine; and a common base on which the gas turbine, the inlet plenum, the exhaust plenum, and the enclosure are mounted. When moving the gas turbine, the gas turbine module is moved together.

An attachment device attaches a plurality of attachment target members to an attachment portion formed in a circumferential direction of a rotating main body portion. A first measurement unit measures a physical amount concerning a perimeter of the attachment portion. An attachment unit attaches, to the attachment portion, the plurality of attachment target members selected based on the physical amount concerning the perimeter measured by the first measurement unit. A second measurement unit measures a physical amount concerning a gap between the adjacent attachment target members to be attached by the attachment unit.

Various embodiments include methods for performing maintenance on a gas turbine bearing area. In some cases, a method includes: separating sections of an inlet bellmouth of the gas turbine without removing the sections of the inlet bellmouth from the gas turbine; removing a housing from over a bearing of the gas turbine; mounting a bearing maintenance apparatus adjacent the inlet bellmouth and the bearing; and performing maintenance on the bearing area while the sections of the inlet bellmouth remain separated.

An apparatus for disassembling and assembling a lower vane carrier and a method for disassembling and assembling the lower vane carrier by using the apparatus are proposed. The apparatus includes a rolling jig that is mounted on the lower vane carrier mounted inside a lower turbine casing, a bolt member that passes through a region where the rolling jig and the lower vane carrier are in contact with each other, and a block member mounted adjacent to the bolt member and configured to prevent the bolt member from being separated.

A device for assembling a turbine engine is configured for centering a shaft of a second module relative to a longitudinal axis of a hollow hub placed in front of a first module, the first module including a longitudinal cavity opening at the front into the hollow hub and passing through the first module until a rear end, the shaft configured to be inserted into the longitudinal cavity. The device includes a centering element and a guiding tube. The centering element is configured to be placed in the hollow hub. The guiding tube is configured to enter into at least one portion of the longitudinal cavity of the first module. The device is arranged so that the guiding tube slides inside the centering element. The invention also relates to the assembly formed by the device and a calibration jig, as well as an assembly method using same.

A method is provided for disassembling a gas turbine engine. The gas turbine engine includes a compressor section, a combustor section, a turbine section, a static structure and a bypass duct. The static structure houses and supports the compressor section, the combustor section and the turbine section. The static structure includes a turbine support structure. The bypass duct includes an inner duct wall, an outer duct wall and a bypass flowpath formed radially between the inner duct wall and the outer duct wall. The outer duct wall extends axially along the static structure and overlaps the turbine support structure. During the method, the turbine support structure is removed from the gas turbine engine while the outer duct wall remains installed.

A lift assembly includes an upper rail. A plurality of rail flanges extend from the upper rail. The lift assembly further includes a plurality of combustion can support assemblies spaced apart from one another. Each combustion can support assembly of the plurality of combustion can support assemblies includes a support flange slidably coupled to a rail flange of the plurality of rail flanges, an outer sleeve, and an inner sleeve assembly configured to removably couple to a combustion can of the turbomachine. Each combustion can support assembly of the plurality of combustion can support assemblies defines a cylindrical coordinate system having an axial direction, a radial direction, and a circumferential direction. Each combustion can support assembly of the plurality of support assemblies is configured to move along any of the axial direction, the radial direction, or the circumferential direction relative to the upper rail.

A manufacturing system manufactures a rotating assembly by attaching a plurality of attached target members in a circumferential direction of a rotating main body portion. A storage member capable of storing the plurality of attached target members is placed on a stand. A measurement device measures a physical amount of the attached target member An attachment device attaches one attached target member to a predetermined position in the circumferential direction of the rotating main body portion based on the physical amount measured by the measurement device A transfer device transfers the attached target member.

A phase adjustment system 100 for a geared compressor 1 includes a phase adjustment jig 50 that is to be detachably provided in the geared compressor 1. The geared compressor 1 includes a drive gear 4 fixed to a drive shaft and having a largest outer diameter among a plurality of gears; a driven gear having a smaller diameter than a diameter of the drive gear 4 and meshing with the drive gear 4; and a gear casing accommodating the drive gear 4 and the driven gear. The phase adjustment jig 50 includes a fifth jig gear 66 that meshes with the drive gear 4 in a state where a frame 51 is fixed to the gear casing; and a manually rotatable handle 70 that is configured to rotate the fifth jig gear 66.