An assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a first annular case that has a first body extending from a first end portion and a second annular case that has a second body extending along a longitudinal axis from a second end portion. The first end portion has a first flange. The first flange has at least one mounting assembly. The at least one mounting assembly has a first aperture dimensioned to receive a fastener and a first ramped surface that extends axially from the first aperture. The second end portion includes at least one flange that defines a receptacle dimensioned to receive the first end portion and a second aperture dimensioned to receive the fastener and a second ramped surface. The first annular case is moveable in an axial direction relative to the longitudinal axis through an axial opening of the receptacle such that the first end portion is received in the receptacle, and is rotatable about the longitudinal axis to define an interface between the first and second ramped surfaces to interlock the first end portion in the receptacle and limit movement of the first annular case relative to the longitudinal axis. A method of assembly for a gas turbine engine is also disclosed.

A locking spacer assembly for filling a final spacer slot in a disk groove between platforms of adjacent blades of a blade assembly in an industrial gas turbine engine is presented. The locking spacer assembly includes a first side piece, a second side piece, a mid piece and a bolt. The bolt is disposed into the mid piece to position the mid piece in a radial position in an assembled state. The mid piece contacts the first side piece and the second side piece in the assembled state to prevent axial movements of the first and second side pieces in the disk groove. The bolt prevents a radial movement of the mid piece.

A locking spacer assembly for filling a final spacer slot in a disk groove between platforms of adjacent blades of a blade assembly, a blade assembly and a method for installing a locking spacer assembly into a final spacer slot in a disk groove between platforms of adjacent blades of a blade assembly are presented. The locking spacer assembly includes a first side piece, a second side piece, a bolt and a mid piece. The mid piece includes a hollow cylindrical body to receive the bolt and a top platform to flush with top surfaces of the first and second side pieces and a middle platform disposed at bottom of the hollow cylindrical body. At least two pins are radially inserted through apertures of the first and second side pieces respectively extending toward the middle platform of the mid piece to prevent radial movement of the mid piece.

An axially divided inner ring is provided for fastening to, in particular adjustable, guide vanes (50) of a turbomachine, in particular a compressor or turbine stage of a gas turbine, which includes a first partial ring (10) and a second partial ring (20), which is supported in the axial direction directly or indirectly on two axially facing support surfaces (11, 12) of the first partial ring (10) and is fixed on the first partial ring (10) in the radial direction with the aid of multiple alignment pins (40) distributed in the circumferential direction.

A monitoring sensor for a state of a blade of a rotating machine includes a sensor for monitoring a state of the blade of the rotating machine, a first section configured to be fixed to a casing of the rotating machine, and a second section holding the sensor and supported by the first section so as to be able to adjust a position of the sensor in an axial direction of the casing.

A coupling system for a machine assembly and a base is provided. The machine assembly includes a frame and a gib key extending outwardly from the frame. The coupling system includes at least one u-bracket configured to couple to the gib key such that said at least one u-bracket cooperates with the gib key to define a tenon pin opening. The at least one u-bracket is sized and shaped to be received in a clearance fit in a key channel defined in the base. The coupling system also includes a tenon pin sized and shaped to be received in the tenon pin opening such that the tenon pin couples the base to the gib key, and such that forces exerted on the received tenon pin parallel to a first direction are substantially in tension between the machine assembly and the base.

Methods of manufacturing a bladed stator element for a turbomachine include mounting a tool on a circumferential zone of an annular shell prior to welding vanes in the circumferential zone, welding radially outer ends of the vanes to the annular shell, dismantling the tool after welding the vanes in the circumferential zone, and repeatedly mounting and dismounting the tool on different circumferential zones of the annular shell so as to fix the vanes all around the annular shell.

An apparatus for handling a turbomachine part, particularly during disassembling and reassembling operations. More specifically, an apparatus for handling the stator cone of a gas turbine suitable to completely manipulate the stator cone during disassembling and reassembling operations. The apparatus allows to disassemble and reassemble the stator cone of a gas turbine without the need to dismount the turbomachine enclosure and without the necessity to have personnel inside the turbomachine package during the operations.

An alignment apparatus for aligning inlet guide vanes in a turbine having a turbine axis includes a tool body, a positioning block secured to the tool body, and a plurality of alignment pieces secured to the tool body. The positioning block may be affixed to the tool body such that when the positioning block is engaged with a leading edge of one of the inlet guide vanes, at least a portion of the alignment pieces is parallel to the turbine axis. The alignment pieces may be manually displaceable from the OFF position to the ON position into engagement with the inlet guide vanes to align one or more of the inlet guide vanes.

The present disclosure is directed to an adjustable mounting assembly for a fan motor, having a frame defining a space configured to receive the fan motor, a fixed nut coupled to the frame, and a bolt extending through the fixed nut and into the space. The frame is configured to mount to a heating, ventilation, and/or air conditioning (HVAC) unit, and the bolt is adjustable relative to the fixed nut to adjust a position of the fan motor within the space.