A method for installing a compressor and a gas turbine of a first type at a position of an existing power plant where previously a compressor and a gas turbine of a second type were installed on a foundation specially designed for the second type. The two types differ from each other at least with respect to the position and/or the number of anchoring points at which the compressor and the gas turbine are connected to the foundation via support structures. The installation of the new compressor and the new gas turbine is carried out using an adapter structure on the existing foundation. A corresponding adapter structure is provided.

A mid-turbine frame (MTF) assembly having: an outer case circumferentially extending around a central axis; an outer ring secured to the outer case and disposed radially inwardly of the outer case relative to the central axis; an inner case structurally connected to the outer case and disposed radially inwardly of the outer ring relative to the central axis; a main plenum circumferentially extending around the central axis and located between the outer case and the outer ring, the main plenum having an inlet fluidly connectable to a source of cooling air, a first outlet fluidly connected to a secondary plenum between the main plenum and the inner case, a second outlet configured to be fluidly connected to a rotor cavity of the low-pressure turbine, and a third outlet configured to be fluidly connected to a plenum surrounding a containment ring of the low-pressure turbine.

A method for manufacturing a turbine engine part in which a first rough casting element includes a first face and a second face opposite to each other is assembled by the second face on an orifice which has a second element of the part. The method includes machining a through-cavity in the first element which opens at the first face and from the second face of the first element and machining the first face of the first element so as to form an area suitable for ensuring the attachment of a conduit on the first element. The machining of the cavity and of the first face is achieved by using a machining reference frame based on the second element.

The invention concerns an inter-blade profile (14) for a turbine runner blade, said inter-blade profile (14) comprising a profile (16), and a plug (18), forming a basis of the profile (16) and intended for being inserted into a corresponding hole (21) made in a blade.

A method of manufacturing a motoring system for a gas turbine having the steps of: assembling a pinned mechanical fuse, the pinned mechanical fuse including at least one shear pin; forming an outer housing; installing a reduction gear train into the outer housing, the reduction gear train having an input and an output; operably connecting a motor to the input; operably connecting a clutch to the output using the pinned mechanical fuse, the clutch in operation engages and disengages the reduction gear train; operably connecting a starter to the clutch, the starter having an output shaft; and operably connecting an accessory gearbox to the output shaft of the starter. The clutch is operably connected to the accessory gearbox through the starter and the output shaft. The at least one shear pin in operation shears when torque on the pinned mechanical fuse is greater than or equal to a selected value.

The invention relates to an assembly (1) for a turbomachine comprising: a first rotor module (2) comprising a first blade (20), a second rotor module (3), connected to the first rotor module (2), and comprising a second blade with a length less than the first blade (20), and a damping device (4) extending with at least one component along a turbomachine longitudinal axis (X-X), characterized in that the damping device (4) is annular while extending circumferentially around the turbomachine longitudinal axis (X-X) and in that the damping device (4) comprises a first radial external surface (40) supported with friction against the first module (2) as well as a second radial external surface (42) supported with friction against the second module (3), so as to couple the modules (2, 3) in order to damp their respective vibrational movements during operation.

A vane for a gas turbine engine, the vane including a platform with an airfoil extending radially from the upper surface of the platform. The platform includes a joint portion which includes a circumferentially extending flange and a recessed surface both formed on either the upper or lower surface of the platform. The flange and the recessed surface extend from opposing circumferential edges of the joint portion and each include a substantially radially-extending through hole.

Provided is a rotating body, including: a shaft; and a compressor impeller including: a main body having an insertion hole, which extends from one end to another end side and is configured to receive the shaft inserted therethrough; a boss portion formed at one end side of the main body; and a joint portion, which is formed on an inner peripheral surface of the insertion hole at the boss portion and is welded to the shaft.

A method for constructing a nozzle ring for a turbocharger turbine nozzle includes the steps of: providing a nozzle ring in the form of an annular flat disk, the nozzle ring having a first face and an opposite second face; forming a plurality of circumferentially spaced circular bores extending through the nozzle ring from the first face to the second face; providing a plurality of vanes, each vane having a circular vane shaft extending from one end of the vane; inserting the vane shafts respectively into the bores in the nozzle ring from said first face thereof and orienting each vane to achieve a desired setting angle for the vane; and rigidly affixing the vane shafts to the nozzle ring to fix the vanes at the desired setting angles.

A bearing chamber housing (20) for bearing a shaft (3) of a turbomachine (1), including a housing outer shell (21) that delimits an oil chamber (33) of the bearing chamber housing (20) radially outwardly in relation to a rotational axis (4) of the shaft (3), and a housing inner shell (22) for bearing the shaft (3). The housing inner shell (22) is radially connected to the housing outer shell (21) via support ribs (23) that in each case extend axially, at least in part, and the housing inner shell (22), the housing outer shell (21), and two support ribs (23) that are next-adjacent to one another jointly delimit a cavity (41) that is axially open at the rear, and thus lead into a rear opening (32). The rear opening (32), viewed in tangential sections, has a clearance (35) in each case that constitutes at least 50% of a circumferential distance (43) between the next-adjacent support ribs (23).