In this method for mounting a combustor component, a component hanging step for attaching a string material to a hanging jig mounted on a combustor component and hanging the combustor component with the string material together with the hanging jig, and a component mounting step for mounting a mounting flange of the combustor component at a combustor mounting position of a gas turbine casing are executed. The hanging jig has a hanging tool having a portion which becomes a suspension point contacted by the string material when the string material is attached and hanging the combustor component. The suspension point is positioned on the distal end side of the center of gravity of the combustor component in the combustor axial line direction when the hanging jig has been mounted to the mounting flange.

In the compressor of a gas turbine engine, variable guide vanes are adjusted by virtue of connections to an actuation ring that can be rotated within a fixed range of degrees. The connections between the guide vanes and the actuation ring can undergo significant torsional stress. Accordingly, an actuation system is disclosed for reducing the torsional stress experienced by the actuation connections.

Various methods and systems are provided for a radial turbocharger. In one example, the turbocharger comprises a turbine case housing a turbine wheel and a compressor case housing a compressor wheel, the turbine case including a vaneless turbine nozzle integrated into the turbine case, a bearing case surrounding a shaft connecting the turbine wheel to the compressor wheel and arranged between the turbine case and compressor case, a plurality of long bolts arranged around a circumference of the turbine case, and a plurality of slots arranged around a circumference of the turbine case, a slot length of each slot extending in a radial direction and adapted to receive a dowel pin having a diameter smaller than the slot length, where each dowel pin, via a corresponding slot, couples the bearing case to the turbine case.

A water heating device equipped with a housing, a fan and a chamber arranged in the interior of the housing, and screws. The housing has first and second side plates which oppose one another in a first direction and extend from the ends of a back plate along a second direction intersecting the first direction. An opening part is provided in the housing on the side opposite the back plate in the second direction. The fan has a discharge opening, a first flow passage extending along the first direction, and a first flange. The chamber has an intake opening, a second flow passage extending along the first direction, and a second flange. The first and the second flanges are secured by screws. In a planar view, the center axis of the screws is slanted such that a head portion is closer to the opening part than the tip-end portion.

A device for attaching a connecting rod small end for a thrust reversal cascade flap onto a fixed internal structure of a turbojet engine nacelle includes a fitting configured to be fixed to the internal structure and a connection interface forming a joint between the connecting rod small end and the fitting. The device further includes a removable fork configured to cooperate with the connection interface, wherein the fork and the connection interface are arranged inside the fitting.

Turbine (1) comprising a casing, an outer metal shroud (9), an inner metal shroud (5) and an annular distributor (2) having a plurality of CMC ring sectors (20), each sector comprising a mast (6), an inner platform (24), an outer platform (26) and at least one blade (28) having a hollow profile that defines an inner housing (280), the inner and outer platforms each having an opening (245, 265) communicating with said inner housing, and the mast (6) passing through said openings and the inner housing and being secured to said casing and connected to said annular sector. Each blade comprises at least one first radial shoulder (72) projecting axially towards the inside of the blade, and each mast comprises at least one second shoulder (71) projecting axially towards the outside of the mast (6) configured to radially cooperate with a first shoulder (72) and radially press the blade (28) against the mast (6).

An assembly for a turbomachine turbine includes at least one ring sector made of CMC material and a support casing including an upstream flange and a downstream flange between which each ring sector is disposed, each ring sector including a base that has a radially external face from which radially extend two lugs, the lugs of each ring sector being retained between the two flanges of the support casing by axial pins each engaged in one of the flanges of the ring support casing and in the lug of the ring sector facing said flange, the assembly further including, for each ring sector, at least one radial retaining pin screwed into the support casing and coming to radially bear against a lug of the at least one ring sector to retain it in position, and anti-rotation system for rotationally locking the radial retaining pin.

A vacuum pump and a damper for the vacuum pump are provided so as to increase vibration isolation in a twisting direction with a simple structure and prevent rupture of an O-ring and an elastic member by regulating a misalignment of flanges facing each other. Provided are a first flange and a second flange, each having a central opening, the flanges being shaped like rings opposed to each other; an O-ring and an intermediate ring that are disposed between the first flange and the second flange; O-rings disposed between the first flange and the intermediate flange and between the intermediate ring and the second flange; a plurality of elastic members that are disposed between the first flange and the second flange and are spread in the circumferential direction of central openings; and airtightness keeping means including positioning pins inserted into positioning holes sequentially provided on the first flange, the intermediate ring, and the second flange.

A turbine shroud assembly adapted for use with a gas turbine engine includes a carrier, a seal segment, and a mount assembly. The carrier is configured to be coupled to a turbine case. The seal segment is shaped to define a gas path boundary of the shroud assembly. The mounting assembly is configured to couple the seal segment to the carrier.

An apparatus for disassembling and assembling a lower vane carrier and a method for disassembling and assembling the lower vane carrier by using the apparatus are proposed. The apparatus includes a rolling jig that is mounted on the lower vane carrier mounted inside a lower turbine casing, a bolt member that passes through a region where the rolling jig and the lower vane carrier are in contact with each other, and a block member mounted adjacent to the bolt member and configured to prevent the bolt member from being separated.