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 power generation transport includes a gas turbine, an inlet plenum coupled to an intake of the gas turbine, a generator driven by the gas turbine, and an air intake and exhaust module including an air inlet filter housing, an intake air duct coupled to the housing at a first end and to the inlet plenum at a second end, and an exhaust collector coupled to an exhaust of the gas turbine. The transport further includes at least one base frame. The frame mounts and aligns the gas turbine, the inlet plenum, the generator, and the air intake and exhaust module. The intake air duct is mounted on the base frame so as to be disposed underneath the gas turbine, and extend along the base frame from an exhaust end side of the gas turbine to an intake end side, in a longitudinal direction of the power generation transport.

A turbine exhaust unit supporting device that supports a turbine exhaust unit is provided. The turbine exhaust unit supporting device installed at a rear side of a turbine casing to support a turbine exhaust unit through which exhaust gas passing through a turbine is discharged, the supporting device includes a casing supporting block unit installed on an outer circumferential surface of the turbine casing, an exhaust unit supporting block unit spaced apart from the casing supporting block unit and installed on an outer circumferential surface of the turbine exhaust unit, and a rotary coupler including a first end rotatably coupled to the casing supporting block unit and a second end rotatably coupled to the exhaust unit supporting block unit.

A shroud assembly adapted for use with a gas turbine engine includes a seal segment, a carrier, and a mount system. The seal segment extends circumferentially at least partway around an axis to define a gas path boundary of the shroud assembly. The carrier is configured to support the seal segment in position radially relative to the axis. The mount system couples the seal segment with the carrier.

An assembly for mounting an auxiliary component to an engine case of a gas turbine engine includes a support bracket, the support bracket having a first end configured for attachment to a first flange of the engine case, a second end configured for attachment to a second flange of the engine case, and an intermediate portion located intermediate the first end and the second end; a bearing member disposed within the intermediate portion; a locator disposed within the bearing member; a first plurality of bolts configured to attach the first end of the support bracket to the first flange; a second plurality of bolts configured to attach the second end of the support bracket to the second flange; and a mechanical fuse.

An assembly for mounting an auxiliary component to an engine case of a gas turbine engine includes a support bracket, the support bracket having a first end configured for attachment to a first flange of the engine case, a second end configured for attachment to a second flange of the engine case, and an intermediate portion located intermediate the first end and the second end; a bearing member disposed within the intermediate portion; a locator disposed within the bearing member; a first plurality of bolts configured to attach the first end of the support bracket to the first flange; a second plurality of bolts configured to attach the second end of the support bracket to the second flange; and a mechanical fuse.

An assembly for mounting an aircraft engine to an aircraft includes an engine casing flange having a first annular wall extending radially to terminate at an annular rim. A second flange of an additional engine component mounted aft of the engine casing includes a second annular wall. An aft mount bracket has an annular body extending uninterrupted about the center axis and a spigot extending axially from the annular body, the spigot extending circumferentially about an entire circumference of the annular body. The aft mount bracket is axially disposed between the engine casing flange and the additional engine component, with corresponding holes in the first annular wall, second annular wall and aft mount bracket being circumferentially aligned, and the spigot radially abutting the annular rim of the engine casing flange.

Devices, systems, and methods for alignment of gas turbine engine components including frame components.

A hanging structure for a wall fan, able to hang a wall fan on a wall, includes a board and a casing. The board to be locked on a wall is provided thereon with at least one first hanging member and at least one first locking member. The casing is provided therein with at least one second hanging member by which the casing can be hung on the first hanging member of the board. The casing is further provided with at least one second locking member to be locked together with the first locking member of the board to have the casing firmly fixed on the board and roughly covering the board. The hanging structure for a wall fan of this invention can simplify aligning, positioning and locking operation and can be firmly hung on a wall to avoid displacement for attaining effect of protection of the wall fan.

Embodiments of a power generation system and methods to be used in conjunction with a high-powered turbine engine are disclosed. The power generation system includes a turbine engine having an exhaust diffuser section installed on the exhaust duct of the turbine engine and a turbine engine exhaust stack assembly connected to the turbine engine exhaust diffuser section. An embodiment further includes thermo-electric generator (TEGs) sub-assemblies connected to the turbine engine exhaust stack assembly. In other embodiments electrical storage devices such as batteries are used.