A filter frame is removably attachable to a box fan. The filter frame is adapted for receiving a standard HVAC-style filter for removing contaminants from air flow induced by the fan. In this manner, a cost-effective means for filtering a flow of air is provided for residential and commercial settings. The filter frame is adaptable to a variety of standard box fan types of different styles and dimensions. The frame is configured to accommodate standard filters, such as those readily available from retail hardware stores and home centers.

A rigid electrical raft is provided to a gas turbine engine via a fusible mount arrangement. The rigid electrical raft may be a part of an electrical system of the gas turbine engine, for example a part of the electrical harness. The fusible mount is arranged to break when a predetermined load is applied. The rigid electrical raft may be attached to a fan case of the engine, and the predetermined load may be that which results from a fan blade being released from the hub. This ensures that the rigid electrical raft is protected from the load.

Turbine engine, comprising means for absorbing the thrust forces from its engine, which comprise longitudinal connecting rods, the ends of which are connected to structural annular casings of the turbine engine, characterized in that it comprises means for supporting at least one item of equipment on said thrust-absorbing connecting rods and/or for suspending at least one item of equipment from said thrust-absorbing connecting rods.

Methods and tools for facilitating the installation and/or removal of a rotor on a shaft of a gas turbine engine are provided. The tool includes a stabilizer attachable to the shaft and including a first guide counterpart. The tool also includes a holder attachable to the rotor and including a second guide counterpart for engagement with the first guide counterpart of the stabilizer. Engagement of the first and second guide counterparts guides movement of the holder relative to the stabilizer along a guide axis and prevents movement of the holder relative to the stabilizer transverse to the guide axis.

A turbomachine assembly for an aircraft comprising a nacelle with a nacelle structure, cowls attached to the structure to create an aerodynamic surface, an articulated cowl, comprising four edges, in the upper portion of the nacelle, an articulation at a first edge of the articulated cowl attached between the articulated cowl and the nacelle structure allowing the articulated cowl to move between a closed and an open position, a locking system at a second edge of the articulated cowl, opposite the first edge. The locking system comprises a handle actuable from the exterior of the nacelle, between a first position and a second position, a locking device movable between a locking position and an unlocking position, and a transmission system that moves the locking device from the locking position to the unlocking position when the handle passes from the first position to the second position, and vice versa.

A mounting system for supporting rotating machinery is described. The system comprises a base frame having an upper side for mounting the rotating machinery, and a lower side. A set of main supporting members are arranged according to a triangular arrangement and forming a three-point mounting arrangement defining a mounting plane. Moreover, a set of auxiliary supporting members, having a variable stiffness in at least one direction, are provided and are configured and arranged such as to increase the stiffness thereof when the base frame is subject to an overload, thus reducing load on the main supporting members.

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).

The invention relates to a mounting assembly with a spherical bearing for mounting a rocket engine and a rocket having such mounting assembly. The spherical bearing includes a spherical bearing base, a spherical retaining ring and a suspension link with a spherical end arranged in a space between the spherical bearing base and the spherical retaining ring. The spherical bearing base is part of an injector head of the rocket engine or is part of a fuel tank, the parts having a spherical shape.

The present invention discloses a system for providing mobile power, in which the required equipment for the power supply system at fracturing fields as well as connection cables and connection hoses are integrated properly, assigned onto three transport vehicles for movement and effectively connected. Intake components and a turbine generation system are combined on a first transport vehicle and installed together, then transported to customer sites directly, thus saving the installation time at the user sites. The two different designs on the locations of an exhaust stack and an exhaust silencer not only meet the requirements of road transportation, but also meet the requirements of exhaust gas emission during operations.

A vane configured to be disposed in a gas path defined in part by an inner surface of a case of a gas turbine engine is provided. The vane comprises a vane body configured to extend through an aperture in the case and a vane head disposed at an end of the vane body. The vane head has an abutting surface configured to contact an outer surface of the case when the vane body extends through the aperture, and a groove configured to receive a sealing member. The groove opens to the abutting surface and is outwardly open relative to an inner region surrounded by the groove. The groove has an inner seating surface that hinders movement of the sealing member toward the abutting surface and can facilitate installation of the vane in the engine.