A sensor for monitoring rotors includes a rotating shaft coupled to a set of rotor blades and a non-rotating tube at least partially disposed within the rotating shaft and coupled to the rotating shaft. The non-rotating tube includes a first end and a second end, a sensor mount disposed within the non-rotating tube proximate to the second end of the non-rotating tube. One or more sensors are attached to the sensor mount.

A hover-capable aircraft is described that comprises a drive unit, a rotor and a transmission interposed between the drive unit and the rotor; the transmission comprises a gear; the gear, in turn, comprises a main body rotatable about a first axis and a plurality of first teeth projecting in a cantilever fashion from the main body; the gear comprises a first pair of first rings axially opposite to each other and cooperating with the gear so as to exert a radial force on the gear.

A hover-capable aircraft is described that comprises a drive unit, a rotor and a transmission interposed between the drive unit and the rotor; the transmission comprises a gear; the gear, in turn, comprises a main body rotatable about a first axis and a plurality of first teeth projecting in a cantilever fashion from the main body; the gear comprises a first pair of first rings axially opposite to each other and cooperating with the gear so as to exert a radial force on the gear.

A power transmission system includes a shaft, a stator disposed within the shaft and substantially concentric with the shaft; and at least one supporting element positioned between the stator and the shaft and configured to support the shaft on the stator to reduce a vibration of the shaft and allow the shaft to rotate relative to the stator. A gas turbine engine including the power transmission system is also described.

A double-ring rotary wing spherical cabin aircraft includes a spherical cabin; an upper protective cover; a lower protective cover; a rotary wing fixing ring connected between inner circles of the upper and lower protective covers, and mounted with a gyroscope and a rotatable attitude-adjusting ring; an upper rotary wing rotor and a lower rotary wing rotor rotationally mounted on the rotary wing fixing ring; and a control system. The spherical cabin is rotationally mounted in the attitude-adjusting ring. Two attitude-adjusting articulated shafts opposite to each other are connected between the attitude-adjusting ring and the rotary wing fixing ring. Two cabin articulated shafts opposite to each other are connected between the spherical cabin and the attitude-adjusting ring. The attitude-adjusting articulated shaft and the cabin articulated shaft are in transmission connection with an attitude-adjusting motor. The attitude-adjusting motor and the gyroscope are electrically connected to the control system.

Embodiments are directed to solid lubricant assemblies for providing over temperature protection for bearings and gears in rotorcraft systems. A solid lubricant enters a fluid state above a certain temperature and is positioned so that fluid lubricant is applied to the bearings or gears.

Embodiments are directed to solid lubricant assemblies for providing over temperature protection for bearings and gears in rotorcraft systems. A solid lubricant enters a fluid state above a certain temperature and is positioned so that fluid lubricant is applied to the bearings or gears.

A coaxial split torque gearbox comprises a first pinion meshed with a first gear; a second pinion attached to the first gear and meshed with a first bull gear, the first bull gear operable for transferring torque to cause a first rotor to rotate; and a third pinion attached to a second gear and meshed with a second bull gear, the second bull gear operable for transferring torque to cause a second rotor to rotate, the second gear being meshed with the first gear, and a number of teeth of the first gear being different than a number of teeth of the second gear.

A coaxial split torque gearbox comprises a first pinion meshed with a first gear; a second pinion attached to the first gear and meshed with a first bull gear, the first bull gear operable for transferring torque to cause a first rotor to rotate; and a third pinion attached to a second gear and meshed with a second bull gear, the second bull gear operable for transferring torque to cause a second rotor to rotate, the second gear being meshed with the first gear, and a number of teeth of the first gear being different than a number of teeth of the second gear.

Aircraft turbomachine including a centrifugal compressor, a combustion chamber, the combustion chamber being supplied by the compressor via a diffuser and via a straightener, and a heat exchanger, the exchanger including a first circuit, supplied with exhaust gas from the turbomachine, and a second circuit, which are connected by volutes on the one hand to an outlet of the diffuser and on the other hand to an inlet of the straightener, the volutes having reversed winding directions such that their connection ports to the exchanger are independent of one another and are substantially diametrically opposed, and such that the minimum cross section of each duct is situated at a larger cross section of the other duct.