A forced induction device for an internal combustion engine is provided, which includes a shaft, and a compressor wheel that is threadably mounted to the shaft, and a tool that is configured to engage one or more through bores in the compressor wheel to thread and unthread the compressor wheel onto and off of the shaft. The compressor wheel has a plurality of blades with leading edges that converge at an apex. The apex is aligned with a centerline of the shaft. The tool allows a technician to rotate the compressor wheel relative to the shaft to install or remove the compressor wheel from the shaft without applying any pressure to the blades of the compressor wheel. An associated assembly method is also provided.

A method of assembling a mobile electric power generation system comprises providing a generator trailer having an electric generator, a gas turbine trailer having a gas turbine, an exhaust trailer having an exhaust device, and an air filter and ventilation trailer having an air inlet device. The method includes positioning each of the generator trailer, the gas turbine trailer, the exhaust trailer, and the air filter and ventilation trailer at a job site such that the generator trailer and the gas turbine trailer are in an end-to-end configuration. The method comprises coupling each of the generator trailer, the exhaust trailer, and the air filter and ventilation trailer to the gas turbine trailer in an operational mode for generating power and decoupling each of the generator trailer, the exhaust trailer, and the air filter and ventilation trailer from the gas turbine trailer in a transport mode for transport.

A wind turbine lifting arrangement includes a tower, a nacelle, a lifting platform and a lifting device attached to the lifting platform for lifting components to be installed in or deinstalled from the nacelle, the nacelle including a main frame attached to a top section of the tower, an attachment portion of the lifting platform being arranged underneath the nacelle and attached to the main frame. The lifting platform includes a lifting device portion provided adjacent to the attachment portion, the lifting device is attached to the lifting platform in the lifting device portion and the lifting device portion and the lifting device are arranged next to a longitudinal side of the nacelle which is one of two opposite longitudinal sides of the nacelle extending along a longitudinal axis of the nacelle and arranged between a top side and bottom side of the nacelle.

A method for manufacturing a compressor includes a step of installing a bundle having an O-ring on an outer peripheral surface inside a lower half casing so that a position of the O-ring in an axial direction coincides with a position of a lower half relief groove, a step of installing an upper half casing having an upper half relief groove on the lower half casing so that a position of the upper half relief groove in the axial direction coincides with the position of the O-ring, and a step of pressing the bundle in the axial direction to move the O-ring to a position away from the lower half relief groove and the upper half relief groove, and bringing the O-ring into contact with the inner peripheral surface of the lower half casing and the inner peripheral surface of the upper half casing.

A seal device includes a first sidewall, a second sidewall and a carbon seal element. The first sidewall is arranged with a first tool die which centers the first sidewall about an axis. The first sidewall axially contacts the first tool die along the axis. The carbon seal element is arranged with a centering element which centers the carbon seal element about the axis. The carbon seal element circumscribes and radially contacts the centering element. The second sidewall is arranged with a second tool die which centers the second sidewall about the axis. The second sidewall axially contacts the second tool die along the axis. The first tool die and the second tool die are moved axially together along the axis to press fit the second sidewall into a bore of the first sidewall and axially capture the carbon seal element between the first sidewall and the second sidewall.

A seal device includes a first sidewall, a second sidewall and a carbon seal element. The first sidewall is arranged with a first tool die which centers the first sidewall about an axis. The first sidewall axially contacts the first tool die along the axis. The carbon seal element is arranged with a centering element which centers the carbon seal element about the axis. The carbon seal element circumscribes and radially contacts the centering element. The second sidewall is arranged with a second tool die which centers the second sidewall about the axis. The second sidewall axially contacts the second tool die along the axis. The first tool die and the second tool die are moved axially together along the axis to press fit the second sidewall into a bore of the first sidewall and axially capture the carbon seal element between the first sidewall and the second sidewall.

The aircraft-engine gas turbine includes an outer sealing ring for sealing an array of rotor blades that can be attached to a housing by a clamping mechanism (80) in a friction fit, and a plurality of ring segments (20.sub.i, 20.sub.i+1), wherein a free axial path length (a.sub.f) of a sealing ring segment counter to the direction of through-flow is at least as large as an axial engagement (a.sub.1) of a rotation locking member (10) of the outer sealing ring (a.sub.f≧a.sub.1), which is free of form fit counter to the direction of through-flow, and/or an axial overhang (a.sub.2) of a radial mounting rail (23) of the outer sealing ring (a.sub.f≧a.sub.2), and/or an axial offset (a.sub.3, a.sub.4) of a sealing fin (31, 41); and/or a quotient of a specific clearance sum of the outer sealing ring attached to the housing in a friction fit.

An aircraft engine repair tool for installing and/or removing a mid turbine frame from a gas turbine engine is provided. The tool includes a stabilizer configured to support a shaft via a load path different from a load path provided by the mid turbine frame rotatably supporting the shaft about a rotation axis. The tool includes a holder attachable to the mid turbine frame, and a guide movably engageable with the shaft and attachable to the holder. The guide guides movement of the holder and of the mid turbine frame relative to the shaft along the rotation axis, and prevents movement of the holder and the mid turbine frame relative to the shaft transverse to the rotation axis when the mid turbine frame is released from the support structure and attached to the holder, and when the holder is attached to the guide.

A system for following the handling of an aircraft engine includes a cradle which supports the engine and stands which are spread out under the cradle. Each stand includes a seating configured to secure the stand on the ground, an actuating cylinder secured to the seating and having a translationally mobile piston, a fixing structure secured to the exterior end of the piston and configured to be fixed to the cradle, and a fluid source which causes the piston to be raised or lowered. Each stand also includes a detector designed to detect an inappropriate movement of the piston and a blocking which blocks the piston from moving when the detector detects an inappropriate movement of the piston. Thus, when an inappropriate movement of the piston is detected, the blocking blocks the movement of the cradle and prevents it from tipping.

Method for replacing, inspecting, and/or repairing components in front bearing region of gas turbine, the gas turbine having at least one fan module, housing, low-pressure system, and high-pressure system, the low-pressure system having low-pressure compressor, low-pressure turbine, connecting shaft, stub shaft, and an N1 shaft connected to the low-pressure compressor via the stub shaft and the connecting shaft, the connecting shaft supported in the housing via first bearing unit, and the stub shaft supported in the housing via second bearing unit, the method including dismounting the fan module, fixing the N1 shaft in an axial direction relative to the housing using fixing device, and dismounting the stub shaft using guide device, the orientation of which relative to the gas turbine in at least one spatial direction is determined by a component of the remaining gas turbine, this taking place after fixing the N1 shaft and after dismounting the fan module.