A method for assembling a plug assembly for plugging one or more ports of a gas turbine engine including that a connector body and a cover operably connected to the connector body are inserted into a sheath through-passage of a sheath. The connector body including a rotatable joint operably connecting the cover to the connector body. The method also includes that a biasing mechanism configured to apply a force to the cover is installed, the cover is rotated relative to the connector body via the rotatable joint, a top housing is slid over the biasing mechanism such that the biasing mechanism abuts a bottom end of the top housing or is located in a cavity defined within the top housing, and the top housing is secured together with the sheath.

It is aimed to improve circularity. In a casing, in which a cylindrical shape thereof is divided into two parts in a radial direction thereof and the casing is connected in the cylindrical shape via flanges thereof protruding outward in the radial direction at both divided ends thereof; increased thickness portions that increase radial direction thickness thereof are formed in a portion excluding the divided ends and circular arc center portions farthest from the divided ends, the portion being between the divided ends and the circular arc center portions.

This steam turbine casing is provided with: a lower half part having a plurality of curved leg parts projecting horizontally around a lower half part body; an upper half part bonded onto the lower half part; a cover member fixed to an upper surface part of the curved leg parts; and curved leg bases each having a lower end part which is placed on a frame and having an upper end part to which a lower surface part of the cover member is fixed, whereby thermal deformation of the casing is suppressed, and a suitable clearance is maintained between the casing and a turbine.

A turbine support structure supports a turbine casing and is configured to be movable when the turbine casing is thermally deformed while a gas turbine is operated, thus preventing a fatigue fracture of the turbine casing from occurring. The turbine support structure includes a pair of supports, each having an upper and lower end, for supporting respective opposite side surfaces of the turbine casing at the upper end of either support; and a movable unit installed at the lower end of each support and configured to movably support the lower end of the support. The movable unit is spaced outwardly from the corresponding opposite side surface of the turbine casing, so that the corresponding support inclines toward the turbine casing and is rotatable. The lower end of each support is rotatably coupled to the corresponding movable unit so that the support is rotatable toward an axis of the turbine casing.

A screw bolt for connecting a lower casing part of a turbine and an upper casing part of a turbine, has a bolt body with a lower end and an upper end, an external thread being arranged on both the lower end and the upper end. A casing for a turbine has a lower casing part, an upper casing part, a screw bolt and two attachment nuts screwed onto ends of the screw bolt, wherein the upper casing part has an upper receiving section and the lower casing part has a lower receiving section of a continuous screw bolt receiving portion for receiving the screw bolt. A turbine has such a casing and a method for assembling such a casing of a turbine.

A mechanical system for a turbomachine includes a turbomachine part to be attached and a plurality of threaded attachment elements mounted on the turbomachine part in sequence along a line. The attachment elements fix the turbomachine part to the turbomachine. At least some of the attachment elements are arranged to be prevented from rotating by mutual cooperation about their corresponding thread axes, by a rotation prevention system provided on each of these attachment elements called self-locking elements. The self-locked elements cooperate in pairs, each pair including two directly consecutive self-locked elements along the line. At least one of the pairs has a distance between the thread axes of its two self-locked elements less than the distance between one of these two thread axes and the axis of either of the two attachment elements arranged along the line on each side of the at least one of the pairs.

A positioning method of an arc-like member according to at least one embodiment of the present invention includes a step of moving a protruding part disposed at a circumferential end of the arc-like member in a radial direction with respect to a reference member positioned on a radially outer side as viewed from the circumferential end of the arc-like member. In the step of moving the protruding part, a wall portion is arranged on a radially outer side or a radially inner side with respect to the reference member, a jack is arranged between the wall portion and the reference member, and the jack is operated to move the protruding part with respect to the reference member by the pressing piece mounted on the wall portion via a rod.

A turbomachine includes a plurality of transition ducts disposed in a generally annular array and including a first transition duct and a second transition duct. Each of the plurality of transition ducts includes an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis, the outlet of each of the plurality of transition ducts offset from the inlet along the longitudinal axis and the tangential axis. The turbomachine further includes a support ring assembly downstream of the plurality of transition ducts along a hot gas path, and a plurality of mechanical fasteners connecting at least one transition duct of the plurality of transition ducts to the support ring assembly.

A multi-component fastener is provided having a body and a sleeve. The body has a shank that extends lengthwise between a head and a distal end. The shank includes a first outer surface. The body includes a first material. The sleeve has a wall defined by an outer surface and an inner surface. The inner surface defines an interior cavity. The wall extends lengthwise between a first end and a second end. At least a portion of the sleeve outer surface contiguous with the first end is threaded. The sleeve includes a second material that is dissimilar to the first material. A portion of the shank including the distal end is disposed within the interior cavity of the sleeve. The sleeve and the shank are fixed to one another.

An engine pod for a gas turbine engine which includes a pod wall having an inside and an outside. The pod wall includes a fixed downstream portion and a displaceable upstream portion which is displaceable in the axial direction between a first upstream position and a second downstream position. At its downstream end facing the fixed portion, the upstream portion forms a radially outer rear edge and axially spaced therefrom a radially inner rear edge, with a recess in between. It is provided that adjacent to the recess, an air-permeable structure is formed in the upstream portion which is intended and configured, in the first upstream position of the displaceable portion, to conduct air flowing in the region of the recess to the inside of the displaceable portion. According to a further aspect of the invention, the axial position of the radially inner rear edge varies in the circumferential direction.