A rotary machine includes a cylindrical rotary shaft extending in a direction of an axis, a fastening bolt having a bolt body that extends in a direction of an axis 0 in the rotary shaft to form fastening portions at both ends, a pair of rotary bodies each having an end portion in the direction of the axis that is fixed to each of the pair of fastening portions to be in contact with an end surface of the rotary shaft in the direction of the axis, and a bolt extension mechanism that temporarily extends the bolt body in the direction of the axis.

An impeller (60) for use in a supercharger (42), which is cable of increasing the efficiency while suppressing the increase in size of the impeller (60), is driven in driving connection with a crankshaft (26) of a combustion engine (E) mounted on a motorcycle to supply an intake air (I) towards the combustion engine (E). When the supercharger (42) is driven at a maximum permissible engine speed of an inlet diameter (Ii), the impeller (60) is so set that the peripheral velocity at an inlet side tip end portion (112) of the impeller (60) may exceed the sonic velocity, and may be smaller than 1.3 times the sonic velocity.

A fan module including variable-pitch blades, a fan rotor bearing the blades of the fan, each mounted to pivot about a pitch axis; a fan shaft extending along a longitudinal axis X inside the fan rotor and driving the fan rotor in rotation. A power shaft drives the fan shaft with a planetary gear speed reducer At least a first and a second bearing guide the rotation of the fan rotor, housed inside a lubrication chamber. A system varies the pitch of the fan blades, including a connecting mechanism connected to the blades of the fan and a controller acting on the connecting mechanism. The first bearing is disposed upstream of the speed reducer and the second bearing is disposed downstream of the speed reducer. The fan rotor is connected to the fan shaft by an annular trunnion extending at least along an upstream portion of the lubrication chamber.

A gas turbine engine for an aircraft includes an engine core including an engine core, a turbine, a compressor, and a core shaft connecting the turbine to the compressor, the turbine comprising a lowest pressure rotor stage, the turbine having a turbine diameter at the lowest pressure rotor stage. A fan located upstream of the engine core, the fan comprising a plurality of fan blades extending from a hub, the hub and fan blades together defining a fan face having a fan face area and a fan tip radius. A ratio of the fan tip radius to the turbine diameter at the lowest pressure rotor stage is in the range from 1.2 to 2.0.

A transmission includes a transmission housing member, a ring portion, a high speed shaft, a third roller, and a third plate bearing, which rotatably supports the third roller. The transmission housing member includes a first supporting surface, which restricts the third roller to a first position, and a second supporting surface, which restricts the third roller to a second position. The third roller is moved within a movement range from the first position to the second position. The movement range includes a specified range in which the third roller is not supported, in a radial direction of the high speed shaft, by the transmission housing member with the third plate bearing in between, but is supported by being held between the ring portion and the high speed shaft.

A pump device for a motor vehicle includes: a pump having a first pump member and a second pump member, the first and second pump members being movable relative to one another; an electric drive having a drive housing and an output shaft rotatable with respect to the drive housing; and a gear mechanism, which couples the output shaft to the first pump member and, by reversing a direction of rotation of the electric drive, is switchable between a first and an opposite second transmission ratio. The gear mechanism has: a planet stage having a planet carrier rotationally fixed relative to the drive housing, and/or first and second freewheels, oppositely directed with respect to one another, and which are arranged axially behind one another, and/or the second pump member has a drive shaft rotatable relative to the output shaft.

A drive system includes a planetary gear set having first and second rotatable input members connected in driven relation with respective first and second power sources, and a rotatable output member connected in driving relation with a working piece, the first and second rotatable input members being connected in differentially rotatable communication with the output member. The input members are operable to vary the rotation and direction of the output member and the connected working piece. In an aspect, the output member is rotatable about an axis for driving the working piece, and the first and second input members are also rotatable about the axis. In a further aspect, the first and second input members include coupling regions for coupling the first and second power sources on-axis with the drive system. In a further aspect, the second power source is a hydraulic input motor concentric with the first input member.

A gas turbine engine includes a fan drive turbine driving a fan rotor through a main gear reduction. A primary lubricant system supplies lubricant to the main gear reduction. An auxiliary oil pump supplies oil to the main gear reduction. An auxiliary pump epicyclic gear train drives the auxiliary pump when the fan rotor is rotating in either direction. The main gear reduction is separate from the auxiliary pump epicyclic gear train.

A gas turbine engine includes a fan shaft that drives a fan that has fan blades. The fan delivers airflow to a bypass duct. A gear system is connected to the fan shaft and is driven through an input defining an input lateral stiffness and an input transverse stiffness. A gear system flex mount arrangement accommodates misalignment of the fan shaft and the input during operation. A frame for supporting the fan shaft defines a frame lateral stiffness and a frame transverse stiffness. The input lateral stiffness is less than 11% of the frame lateral stiffness and the input transverse stiffness is less that 11% of the frame transverse stiffness.

A centrifugal compressor includes a low-speed shaft, an impeller, a speed increaser, a housing, a separation wall, a shaft insertion hole, a seal member, an oil pan, an oil supply passage, an oil return passage, and a pressure reduction passage. The impeller is integrally rotated with a high-speed shaft. The housing has therein an impeller chamber accommodating the impeller and a speed increaser chamber accommodating the speed increaser. The centrifugal compressor includes a bypass passage having a first end communicating with the speed increaser chamber and a second end communicating with the oil pan.