A vane arm assembly for a gas turbine engine is provided including: a vane arm having a first end, a second end opposite the first end, and an aperture proximate the second end, the aperture being defined by an aperture wall; a vane stem extending through the aperture of the vane arm; a mechanical fastener retaining a position of the vane arm in the longitudinal direction of the vane stem; and an impedance clip partially enclosing a portion of the second end of the vane arm to provide redundant position retention of the vane arm in the longitudinal direction of the vane stem.

A planetary gearbox device for a turbomachine, having a planet carrier and at least one planet gear arranged rotatably thereon, is described. The planet gear is arranged in the axial direction between two planet carrier regions, to each of which at least one carrier element, on which the planet gear is rotatably mounted, is connected for conjoint rotation therewith. A wedging sleeve is arranged between the carrier element and each of the planet carrier regions, by means of each of which wedging sleeves a press-fit joint is established between the carrier element and the planet carrier regions. A sleeve is provided radially between at least one of the wedging sleeves and a planet carrier region.

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.

An air bleed device for an aircraft engine, including a frame and a flap able to rotate about an axis in relation to the frame, the device further including a return system configured to bias the flap in a determined position about the axis and including a torsion spring, a first end of which is connected to the flap and a second end of which is connected to the frame, wherein the second end is connected to the frame by adjusting the preload of the spring by screwing when the flap is in the determined position.

An accessory system for a gas turbine engine having a drive shaft with an axis of rotation is provided. Also provided is a bearing housing assembly for coupling the drive shaft of an accessory having a first gear to a gear associated with the accessory system. The bearing housing assembly includes a mount including an interface to be coupled to the accessory and defining a central bore, and a lock cylinder configured to receive the drive shaft. The lock cylinder is movable relative to the central bore and the drive shaft to adjust a contact pattern between the first gear of the drive shaft and the gear of the accessory system.

A stationary-blade-type rotating machine is provided with a rotational shaft, an impeller, an impeller housing having a scroll passage formed on an outer peripheral side of the impeller, a bearing housing connected to the impeller housing in an axial direction of the rotational shaft, a stationary blade disposed in a radial passage formed between the scroll passage and the impeller and defined by an impeller-housing-side member and a bearing-housing-side member which face each other in the axial direction of the rotational shaft. The fixation unit includes an annular circumferential groove formed in an inner peripheral surface of the impeller housing and a ring-shaped fitting member subjected to a force for expanding in a radial direction while being fitted into the circumferential groove. The fitting member is configured to press the stationary blade to the impeller housing via at least one of the impeller-housing-side member or the bearing-housing-side member.

A clearance adjusting apparatus to move a thrust bearing of a gas turbine back and forth to adjust a tip clearance of a turbine is provided. The clearance adjusting apparatus includes an adjusting plate disposed to move forward from or rearward to a reference surface, a biasing cylinder disposed to selectively move the adjusting plate back and forth, a stopper disposed to be moved toward the adjusting plate after being moved forward to prevent a rearward movement of the adjusting plate, a position sensor disposed to measure a distance from the reference surface to the adjusting plate, and a controller configured to receive information about measurements from the position sensor and control an operation of the stopper and the biasing cylinder based on the received information.

A clearance adjusting apparatus disposed in front of a compressor of a gas turbine to axially move a compressor disk back and forth to adjust a tip clearance formed between a compressor blade and a compressor casing is provided. The clearance adjusting apparatus includes a hollow fastening part disposed in front of the compressor casing, a shaft disposed in the fastening part and coupled to a front side of the compressor disk, an adjusting part disposed between the fastening part and the shaft to axially move the shaft back and forth to adjust the tip clearance, and a biasing part disposed on the fastening part to bias the adjusting part back and forth to adjust a position of the adjusting part and the shaft.

A method for shimming a thrust bearing for an accessory power take off shaft to obtain optimal meshing of bevel gears within the internal gearbox (IGB) without disassembly of the IGB is enabled by relocating the thrust bearing from the engine sump. The accessory gearbox (AGB) is driven from a power off-take from the turbine spool via the IGB. The radial position of the power take-off bevel gear is established by a radial position of the thrust bearing attached to the exterior of the casing via a housing. Candidate shims are selected from a set each having different thicknesses, the shims are formed of two halves and placed between the housing and the engine casing to adjust the radial position of the thrust bearing and consequently the power take-off bevel gear, without requiring the disassembly of the IGB.

A method and system for aligning a component within a turbine casing, and a related turbine casing. In a top-on position, a location of an optical target and another, vertically spaced optical target on the joint flange are measured. After removing at least the upper casing, the optical targets' locations are measured again, and the locations of a pair of reference points on an upper surface of the horizontal joint flange are measured. A prediction offset value is calculated for the component support position in the top-on position based on the locations. The prediction offset value may include a vertical adjustment based, in part, on a translation of a triangular spatial relationship of a number of the reference points and/or a tilt angle, a horizontal adjustment, and a horizontal joint flange surface distortion adjustment. Support position is adjusted by the prediction offset value to improve alignment.