Guide systems for installing aircraft structures are disclosed. An example apparatus includes a first guide structured to be supported by a first hinge component of a first aircraft structure and a second guide structured to be supported by a second hinge component of a second aircraft structure. The first guide is to receive the second guide when the second structure is at an installation angle relative to the first structure. Engagement between the first guide and the second guide to enable rotational movement of the first hinge component and the second hinge component when the second aircraft structure moves to an installed position.

Embodiments herein provide a vehicle-mounted gas turbine generator set, including: a chassis vehicle, a main cabin body and at least one of an air intake filter system, a ventilation filter system and an exhaust system. The chassis vehicle includes a main beam and an operator cabin. The operator cabin is located at a first side of the main beam in a first direction. The main cabin body defines a main accommodation space. A gas turbine and a generator connected with each other, and an electrical system connected with the gas turbine and the generator, are arranged in the main accommodation space. In a second direction perpendicular to the first direction, the main accommodation space is located between the main beam and the at least of the air intake filter system, the ventilation filter system and the exhaust system.

The disclosure provides a removable support interface for an annular turbomachine casing, the removable interface having a coupling part configured for being mounted on the casing, and at least one attachment element for suspending the casing, orifices arranged in the coupling part the interface having means for locking the coupling part to the casing.

A drive unit includes an engine such as a turbofan engine and a nacelle which includes, on the outside around an annular stream of fresh air, starting from upstream, an air inlet, front side covers, a thrust reverser having reversal gratings and movable rear covers. The front side covers surround the reversal gratings of the thrust reverser when it is closed, and the movable rear covers retreat with said gratings to open the reverser. The engine includes lifting points that form heavy-duty attachment points intended to receive handling clevis for lifting and transporting the drive unit. The lifting points are two upper lifting points arranged on the engine, each on one side of the engine radially behind the front side covers above the horizontal diameter (D) of the drive unit.

A device for removing and/or installing an annular component, which is arranged at a position within a turbine housing, which position is accessible via an access point of the turbine housing. A method for removing and for installing a component of this type by a device of this type.

A suspending tool includes a suspending tool main body that extends to be parallel with an axial direction above a rotor main body, a pair of bearing supporting portions that are disposed at an interval in the axial direction and are detachable from the bearing portions, a pair of seal supporting portions that are disposed inside the pair of bearing supporting portions in the axial direction at an interval in the axial direction and are detachable from the seal portions, and a plurality of diaphragm supporting portions that are disposed inside the pair of seal supporting portions in the axial direction such that the diaphragm supporting portions are disposed at intervals in the axial direction and are detachable from the diaphragms.

A support system for assembling and shipping a steam turbine is provided that includes an annular support fixture configured to be coupled to a longitudinal end of a casing of the steam turbine. The annular support fixture includes a first protrusion that extends in an axial direction relative to a longitudinal axis of a rotor of the steam turbine between the rotor and the casing and that is configured to support the rotor in the radial direction. The annular support fixture includes a second protrusion, which extends in the radial direction toward a lateral surface of the rotor and which includes a surface configured to face the rotor in the axial direction. The support system includes a block configured to be disposed between the surface of the second protrusion and the rotor, such that the block blocks movement of the rotor in the axial direction during shipping of the steam turbine.

An assembly is provided for an aircraft propulsion system. This assembly includes a fixed structure and a nacelle. The nacelle includes a first fan cowl and a first thrust reverser section adjacent the first fan cowl. The first fan cowl is movably attached to and arranged on a first side of the fixed structure. The first fan cowl is configured to move between a first fan cowl closed position and a first fan cowl second position. The first thrust reverser section is movably attached to and arranged on the first side of the fixed structure. The first thrust reverser section is configured to move between a first thrust reverser section closed position and a first thrust reverser section open position when the first fan cowl is in the first fan cowl closed position.

A modular flooring system comprises a modular floor surface and a plurality of stackable, three-dimensional modular interior design components (MIDCs). The modular floor surface can comprise an array of discrete, raised, low-profile, receiving panels that can be rectangular in shape. MIDCs can be securely and interchangeably placed on any group of one or more adjacent unoccupied receiving panel and they can also be stackable, such that various different floor layouts can be created. Each of the MIDCs may comprise a lower surface recess that fits over a group of one or more adjacent raised receiving panels. A first MIDC may have an raised lip on a top surface such that the lower surface recess of a second MIDC fits over, separately and interchangeably, one (or more) of the raised receiving panels and the raised lip on the top surface of the first MIDC. The MIDCs can comprise a storage cube MIDC (square or rectangular cube) as well as specialized MIDCs, such as a commode MIDC, a sink MIDC, a cooler MIDC, and a tile MIDC, etc. In such a manner, a user of the modular flooring system could locate the MIDCs on the floor surface and/or stack them to configure a preferred layout. Moreover, the MIDCs could be rearranged later to design a new layout.

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.