A gas turbine engine (30) comprising a rear cowl (38) defining an exhaust aperture (40) and a motive system. The rear cowl (38) comprises at least one panel (42) and the motive system is operable to selectively move the panel (42) between deployed and stowed configurations by rotation of the panel (42) about an axis substantially parallel to the main rotational axis of the engine (30). This alters the area of the exhaust aperture (40).

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.

Methods are provided for securing a tool within a gas turbine engine. The method can include inserting a tool into the engine; inserting a bladder between a portion of the tool and a component in the engine; and inflating the bladder to temporarily secure the tool in its position. For example, two tools (or more) can be inserted into the engine and secured by the bladder.

According to one embodiment, a maintenance method includes providing the electric generator with leg plates for placing the electric generator on a floor face of a foundation pedestal, forming a bottom portion of the electric generator to have a bottom plane capable of supporting a weight of the electric generator, and forming a gap between the bottom plane of the electric generator and an opposing floor face of the foundation pedestal; and providing the carrier device in the gap, and lifting up and horizontally moving the electric generator by the carrier device, and thereafter doing maintenance of the electric generator.

An exhaust-side journal bearing for supporting a gas turbine rotor is disposed inside a bearing box. The bearing box is supported by a strut which extends inward from an exhaust casing, and a seal ring having an annular inner peripheral end is disposed on the bearing box. Executed during a maintenance work are: a bearing adjustment step of displacing a bearing surface of the journal bearing relative to the bearing box in a perpendicular direction perpendicular to the axial direction; and a seal ring adjustment step of displacing the inner peripheral end of the seal ring relative to the bearing box in accordance with the direction of displacement and the amount of displacement of the bearing surface.

The present disclosure is directed to an auxiliary cleaning system for cleaning a gas turbine engine. The auxiliary cleaning system includes an external motoring source mechanically coupled to one or more engine shafts of the gas turbine engine. Thus, the external motoring source is configured to turn the one or more shafts. The auxiliary cleaning system also includes a cleaning apparatus configured to implement a cleaning procedure on the gas turbine engine while the external motoring source is turning the one or more shafts of the gas turbine engine.

A gas turbine engine unit (110) for use in a modular power generation system includes an engine package (112) and a mechanical handling system adapted to convey components (114) out of and into the engine package (112). The engine package (112) includes a floor (132), a plurality of side walls (136), and a ceiling (134) that cooperate to define a sheltered space (140) sized to receive a gas turbine engine. The mechanical handling system includes rails (121) adapted to support components (114) conveyed out of and into the sheltered space (140) defined by the engine package (112).

A grid-type thrust reverser for a turbojet engine includes a moving O-shaped thrust reverser body that is generally cylindrical in shape around a longitudinal central axis (A) and includes an inner wall configured to delimit a cold air stream, with an inner structure that surrounds the turbojet engine, the movable thrust reverser body being mounted so as to be able to slide along the longitudinal central axis (A) between a direct jet position in which the outer cowl covers the thrust reverser grids, and a thrust-reversal position in which the outer cowl uncovers the thrust reverser grids. The movable thrust reverser body includes a first half-portion and a second half-portion that are mounted so as to each pivot about a longitudinal pivot axis (B), between a closed position and an open gullwing position for removing the turbojet engine, via the cradle.

A bladed rotor system for a turbomachine includes a circumferential row of blades mounted on a rotor disc, and includes a plurality of under-platform dampers. Each damper is located between adjacent blade platforms. The plurality of dampers includes a first set of dampers and a second set of dampers. The dampers of the first set are distinguished from the dampers of the second set by a cross-sectional material distribution in the damper that is unique to the respective set. Dampers of the first set and the second set are positioned alternately in a periodic fashion in a circumferential direction, to provide a frequency mistuning to stabilize flutter of the blades.

A nozzle box assembly includes steam inlets, through which working steam is supplied, a torus part connected to the steam inlets so as to form an annular steam path and having an opening portion, in which a part of the front surface of the annular steam path is opened, a bridge ring connected to the front surface of the torus part and having a bridge inside, and a steam path ring connected to the bridge ring so as to provide a path, which is connected to a stage, and provided with a plurality of vanes, wherein the bridge ring and the steam path ring are formed of the coupling of a plurality of divisions, which are divided in the circumferential direction thereof, and the divisions are coupled to the front surface of the torus part.