A dual stage blower assembly includes a first fan configured to rotate about the rotational axis and including a first plurality blades. The first plurality of blades include a plurality of backward curved blades. The dual stage blower assembly also includes a second fan circumscribing the first fan and configured to rotate about the rotational axis. The second fan includes a second plurality of blades, wherein the second plurality of blades include one of a plurality of forward curved blades, a plurality of a radial blades, or a plurality of backward curved blades. At least one motor is coupled to the first fan and the second fan and configured to rotate the first fan and the second fan about the rotational axis.

The invention includes a disc-shaped disc section (30) that is attached to a rotating shaft (6), and blade sections (40) that are provided on a front surface (31) that is one side in an axial direction of the disc section (30). Balance holes (33) for attaching weight-adjusting weight members W thereto are provided at positions where the blade sections (40) are provided in a radial direction, in a rear surface (51) that is the other side in the axial direction of the disc section (30).

The present invention relates to a turbine engine comprising a wheel, (2) mounted on a shaft (4), and a disk (18), adjacent to the wheel (2) and mounted on the same shaft while being rotated by the latter. The disk (18) is made of a material having a density greater than that of the material used to manufacture the wheel (2). The invention is of use in a compressor/turbine.

A turbomachine arrangement includes a housing, a turbo-expander formed with an expander rotor, a turbo-compressor formed with a first compressor rotor, and a shaft that is rotatably mounted on the housing. The shaft connects the expander rotor to the compressor rotor. The first turbo-compressor can be driven exclusively by the turbo-expander. A second turbo-compressor having a second compressor rotor is disposed on the housing such that the second compressor rotor is connected to the first turbo-compressor in parallel or in series. The second compressor rotor is driven via a transmission accommodated in the housing and via a drive shaft connecting the transmission to the second compressor rotor.

A gas turbine engine has a fan drive turbine driving a gear reduction, the gear reduction, in turn, driving a fan rotor, the fan rotor delivering air into a bypass duct as bypass air and into a compressor section as core flow. A forward bearing is positioned between the gear reduction and the fan rotor and supports the gear reduction. A second bearing is positioned aft of the gear reduction and supports the gear reduction. The second bearing is a thrust bearing. A fan drive turbine drive shaft drives the gear reduction. The fan drive turbine drive shaft has a weakened link which is aft of the second bearing such that the fan drive turbine drive shaft will tend to fail at the weakened link, and at a location aft of the second bearing.

A compressor including a gear system configured to be driven by a drive unit, a plurality of compression stages coupled to the gear system, wherein the plurality of compression stages includes at least one centrifugal compression stage and at least one positive displacement compression stage, is provided. Furthermore, an associated method is also provided.

An integral transmission for a transmission turbomachine has two gearwheels which are in mesh with a large wheel and which are each connected to a shaft that can be connected to an input and/or output unit. A housing, in which the gearwheels or the shafts connected thereto are supported and at least two partial housing units which can be connected by a main joint that extends through the support region of at least one gearwheel in mesh at least indirectly with the large wheel or of the shaft connected to the gearwheel. Accordingly, one of the two partial housing units is formed from at least three housing parts including a central housing part, which is assigned to the large wheel, and two side housing parts. The central housing part can be connected to an individual side housing part by a joint aligned at an angle to the main joint.

Provided is a compression system including: at least one impeller; a gear train configured to the at least one impeller; a main drive shaft configured to drive the gear train; and a housing comprising an impeller container configured to house the at least one impeller and a gear train container configured to house the gear train.

A compressor system includes a driving unit having a drive shaft, a plurality of compressors which compress a gas, and a transmission mechanism which increases a speed of a rotation of the drive shaft and transmits the rotation to the plurality of compressors. The transmission mechanism includes a main shaft which rotates together with the drive shaft and a plurality of gear mechanisms which transmit a rotation of the main shaft to the corresponding one compressor. The gear mechanism includes an auxiliary shaft which rotates together with an auxiliary gear meshing with the main gear, a plurality of first gears which rotate together with the auxiliary shaft, an output shaft to which an output gear meshing with the first gear is fixed and which is connected to the compressor, and a first bearing which rotatably supports the auxiliary shaft, and a second bearing which rotatably supports the output shaft.

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.