Methods of manufacturing toothed components for gas turbine engines are provided. The methods include forming a first tooth in the component with a top land, a bottom land, a side wall extending therebetween, and a fillet radius transitioning between the side wall and the bottom land, forming a second tooth in the component adjacent the first tooth, the second tooth having a top land, a bottom land, a side wall extending therebetween and facing the first tooth, and a fillet radius transitioning between the side wall and the bottom land, the bottom land of the second tooth extending toward the bottom land of the first tooth, wherein the bottom lands define a gable area of the component, and forming a stress relief feature in the gable area such that the stress relief feature reduces a stress concentration near the gable area during operation of the toothed component.

The present disclosure relates to a spline connection structure in which a shaft portion having teeth with crowned tooth surfaces formed at equal intervals on an outer circumferential surface and a cylindrical portion having grooves into which the teeth of the shaft portion are fitted formed on an inner circumferential surface are connected, wherein two adjacent tooth surfaces facing each other are bent while maintaining a constant distance therebetween in a tooth width direction when viewed from a diameter direction of the shaft portion.

Aspects of the disclosure are directed to a seal comprising: a first fitting configured to couple to a first disk, and a curvic joint including curvic teeth, where a first distance between the first fitting and the curvic teeth is equal to or greater than a first thickness of the first disk. In some embodiments, an engine comprises: a compressor disk, a turbine disk, and a seal including: a first fitting configured to couple to the turbine disk, a second fitting configured to couple to the compressor disk, and a curvic joint including curvic teeth, where a first axial distance between the first fitting and the curvic teeth is greater than or equal to a first radial thickness of the turbine disk.

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.

An exhaust-gas turbocharger (1) having a shaft (2), a turbine wheel (5), which is fastened to the shaft (2), and a heat throttle (8) between the shaft (2) and the turbine wheel. An end face (3) of the shaft (2) is provided with a protrusion (4), with an outside diameter (A.sub.4) which is smaller than the outside diameter (A.sub.2) of the shaft (2). The turbine wheel (5) has a hollow receiving portion (7), which is formed integrally on the wheel rear side (6) and the inside diameter (I.sub.7) corresponds to the outside diameter (A.sub.4) of the protrusion (4) and the outside diameter (A.sub.7) corresponds to the outside diameter (A.sub.2) of the shaft (2). The protrusion (4) engages into the receiving portion (7). The heat throttle (8) is formed by a cavity (8A, 8B), which has an outside diameter (A.sub.8) which is smaller than the outside diameter (A.sub.4) of the protrusion (4) and extends from the protrusion (4) into the receiving portion (7).

An electrical power generation system including a micro-turbine alternator. The micro-turbine alternator including: a combustion chamber, at least one turbine driven by combustion gases from the combustion chamber, a first stage compressor, and a second stage compressor. The first stage compressor and the second stage compressor being operably connected to the combustion chamber to provide a compressed airflow thereto. The micro-turbine alternator including one or more shafts connecting the at least one turbine to the first stage compressor and the second stage compressor such that rotation of the at least one turbine drives rotation of the first stage compressor and second stage compressor. The one or more shafts include a turbine shaft attached to the at least one turbine a compressor shaft attached to the first stage compressor, and a coupling assembly configured to operably connect the turbine shaft to the compressor shaft via a magnetic coupling force.

An insert for supplying a fluid within a drive shaft, the insert extending along an axis of rotation and comprising an insert wall having a rigid inner insert wall portion and an elastically deformable outer insert wall portion a reservoir defined by the insert wall for storing a fluid, a nozzle positioned at the first end of the insert wall, and wherein the elastically deformable outer insert wall portion is configured to move between an expanded state, when the fluid is supplied to the reservoir, and an unexpanded state, when rotation of the insert and supply of fluid to the reservoir are ceased, and movement of the elastically deformable outer insert wall portion to the unexpanded state forces the fluid to be discharged through the nozzle.

A device for axial locking of a moving part in rotation with respect to a reference part, includes a downstream locking wedge provided with lugs laid out such that the downstream locking wedge can be placed in: a first angular position in which the downstream locking wedge may be translated axially with respect to the moving part, a second angular position in which the lugs axially immobilize the downstream locking wedge with respect to the moving part; an upstream locking wedge able to prevent the rotation of the downstream locking wedge with respect to the moving part; and a stop segment able to immobilize axially the upstream locking wedge against the downstream locking wedge.

A power transmission apparatus has a housing, a first shaft rotatably mounted within the housing, a second shaft rotatably mounted within the housing and extending around at least a portion of the first shaft, a third shaft exterior of the first and second shafts and positioned within the housing, a first transmission connected to the second shaft and to the third shaft such that a rotation of the second shaft causes a rotation of the third shaft, a second transmission connected to the first shaft and to the third shaft such that a rotation of the first shaft applies rotational energy to the third shaft, and a power receiver connected to the third shaft so as to convert the rotational energy of the third shaft into energy or motion.

The invention concerns a turbomachine rotor (1), characterised in that it comprises a threaded or tapped part (3, 6) and a damping nut (8) screwed onto the threaded or tapped part (3, 6) so as to allow the threads of the nut (8) and of the threaded or tapped part (3, 6) to rub against each other in the event of vibration of the rotor (1).