An impeller attach mechanism for a turbocharger including a stud extending from a central bore of a compressor impeller toward a turbine wheel, the stud having a first threaded region and a second threaded region; a shaft coupled to the turbine wheel and extending toward the compressor impeller, the shaft having a leading portion, the leading portion having a threaded interior configured to engage the second threaded region of the stud; and an insert having an internal portion and an external portion, the internal portion having a threaded external surface to engage the compressor impeller, the internal portion having a threaded internal surface to engage the first threaded region of the stud, the external portion configured to surround the leading portion of the shaft.

A method for shimming a thrust bearing for an accessory power take off shaft to obtain optimal meshing of bevel gears within the internal gearbox (IGB) without disassembly of the IGB is enabled by relocating the thrust bearing from the engine sump. The accessory gearbox (AGB) is driven from a power off-take from the turbine spool via the IGB. The radial position of the power take-off bevel gear is established by a radial position of the thrust bearing attached to the exterior of the casing via a housing. Candidate shims are selected from a set each having different thicknesses, the shims are formed of two halves and placed between the housing and the engine casing to adjust the radial position of the thrust bearing and consequently the power take-off bevel gear, without requiring the disassembly of the IGB.

Embodiments of the disclosure provide a tool and method for alignment adjustment of machinery. The tool may include a bottom plate, a top plate oriented in parallel planes, a low friction intermediate element between bottom plate and top plate, and a hydraulic actuator or electro-mechanic actuator arranged between the bottom plate and the top plate and capable of moving the top plate relative to the bottom plate.

A system for providing mobile electric power includes a first transport including an inlet plenum and a generator, a second transport including a gas turbine, and a turbine exhaust unit, and a third transport including a generator exhaust air handling system, a combustion air handling system, and a turbine enclosure air handling system. The first transport, the second transport, and the third transport are separate transports that are independently movable in a transportation mode. In an operation mode, the first transport and the second transport are connected to each other such that a first end side of the first transport faces and is connected to a first end side of the second transport, and the inlet plenum mounted on the first transport is connected to an intake of the gas turbine mounted on the second transport. In the operation mode, the third transport is positioned at a predetermined distance relative to the connected first and second transports such that a first longitudinal side of the third transport faces a first longitudinal side of the first transport and a first longitudinal side of the second transport.

A locking spacer assembly for filling a final spacer slot in a disk groove between platforms of adjacent blades of a blade assembly in an industrial gas turbine engine is presented. The locking spacer assembly includes a first side piece, a second side piece, a mid piece and a bolt. The bolt is disposed into the mid piece to position the mid piece in a radial position in an assembled state. The mid piece contacts the first side piece and the second side piece in the assembled state to prevent axial movements of the first and second side pieces in the disk groove. The bolt prevents a radial movement of the mid piece.

a tooling assembly for installation relative to a first and second turbomachine component is provided. The tooling assembly includes an axial mounting portion removably couplable to the first turbomachine component. The axial mounting portion includes a first plate, a second plate spaced apart from the first plate, and at least one turnbuckle assembly that extends between, and is coupled to, the first plate and the second plate. At least one of the first plate and the second plate include a radial compression portion. The radial compression portion includes a compression bar radially movable relative to the axial mounting portion and configured to contact the second turbomachine component.

A tube assembly according to an exemplary aspect of the present disclosure includes, among other things, an adjustable joint having a flange axially movable along an end fitting having a male/female connection with a mating part. The flange is threadably engaged with the end fitting to provide for the adjustment of the position of the flange along the end fitting. The adjustable joint accommodates thermal effects and tolerance stack-up in a male/female connection.

The invention relates to an aircraft turbine engine module (10), comprising a degassing tube (14) and an ejection cone (12). The tube and the cone comprise centring means engaging together. The invention also relates to a locating and adjusting tool for assembling said module.

A multi-ring spacer includes a first ring having a first clocking position, a second ring coaxial with the first ring, and having a second clocking position. A total kink angle of the multi ring spacer is dependent on an angular deviation of the second ring's clocking position relative to the first ring's clocking position.

A turbine shroud assembly for use with a gas turbine engine includes a turbine outer case, a blade track segment, and a carrier assembly. The carrier assembly includes a forward carrier segment and an aft carrier segment, and each of the forward carrier segment and aft carrier segment include integrated pins. The carrier assembly is configured to couple the blade track segment to the turbine outer case.