A nacelle for a bypass turbojet engine includes a cascade thrust reverser provided with reversal cascades arranged around an annular stream of fresh air, beneath front cowls. The cascades move backward with movable rear cowls, opening side passages in the annular stream, which receive the cascades for directing the fresh air flow forward, the bypass turbojet engine. The bypass turbojet engine includes fixing points, and the nacelle includes outer hatches closing openings of the front cowls, which are arranged radially outside the fixing points for access thereto, each hatch opening including a contour with edges of two front cowls.

A method of axially separating an annular system, such as a gas turbine engine (10), comprising first (34) and second (36) annular components. An annular array of fastenings (42) couples the first (34) and second (36) components together axially. The first (34) and second (36) components are supported by support tooling. The fastenings (42) are removed to leave one fastening (42) located on each side of the system. One of the remaining fastenings (42) is removed. The relative height of the first (34) and second (36) components is adjusted so that the apertures (46, 48) for the fastening (42) removed at the previous step are aligned. Then the final fastening (42) is removed.

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.

The embodied invention is a storage frame that supports an aircraft engine with flexible engine mounting and is easily assembled by bolts. It includes feet to anchor the frame to the ground. It has adjustable height legs and is attachable to a variety of engine mount positions. It includes a central lifting tube with lifting connections that allow the frame to be lifted by an overhead crane or forklift. The adjustable legs provide convenience in transferring the engine onto a shipping support stand.

An apparatus for removing or installing a turbine blade from a turbine of a turbomachine is disclosed. The apparatus can include: an operative head configured to engage an axial sidewall of a turbine blade base. An actuator is configured to move the operative head to selectively engage the axial sidewall of the turbine blade base and impart an axial force against the turbine blade base to remove or install the turbine blade. A support gantry is configured to position the actuator substantially vertically above the turbine blade in position in the turbomachine. Among other advantages, the support gantry allows adjustment of the apparatus for different turbines, and use of the head on more than one stage of any given turbine.

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.

The present invention particularly relates to a carrier with movable fan blade holders (2) that can swivel independently in the vertical axis so as to carry and pile up the fan blades and mating parts to be removed from engines or to be mounted thereto during performing maintenance of aircraft engines or repairing process. Furthermore, it is ensured by means of the present invention to index holders (2) through an index mechanism (7) and to fasten the fan blades to holders (2) through a belt (4).

A device for assembling and disassembling a component of a gas turbine, having a rail system with at least two running rails. A carriage which can be pushed on the running rails along a specified movement axis is provided on the running rails, and the carriage has a securing device which is designed to secure a fitting section of a first carriage insert in a force-fitting manner such that the first carriage insert is moved together with the carriage when the carriage is moved on the running rails.

An apparatus for removing or installing a turbine blade from a turbine of a turbomachine is disclosed. The apparatus can include: an operative head configured to engage an axial sidewall of a turbine blade base. An actuator is configured to move the operative head to selectively engage the axial sidewall of the turbine blade base and impart an axial force against the turbine blade base to remove or install the turbine blade. A support gantry is configured to position the actuator substantially vertically above the turbine blade in position in the turbomachine. Among other advantages, the support gantry allows adjustment of the apparatus for different turbines, and use of the head on more than one stage of any given turbine.

A fixture assembly includes a support stand, a support platform and a platform adaptor. The support platform is rotatably coupled to the support stand and rotatable about an axis. The support platform extends circumferentially about a centerline angularly offset from the axis. The support platform extends longitudinally along the centerline to a platform top surface. The platform adaptor is disposed on the platform top surface and attached to the support platform. The platform adaptor includes a case receptacle formed by an adaptor top surface and an adaptor shoulder surface. The platform adaptor extends longitudinally along the centerline to the adaptor top surface where the adaptor top surface is configured to longitudinally engage and support the case. The platform adaptor extends radially relative to the centerline to the adaptor shoulder surface where the adaptor shoulder surface is configured to radially engage and position the case on the adaptor top surface.