A compressor device includes a coolant jacket cooperatively defined by a motor case and an outer motor housing. The coolant jacket includes a radial portion that spans about the motor case in a circumferential direction and an axial direction with respect to the axis of rotation of the motor. The coolant jacket includes an axial portion that spans in a radial direction across an axial end of the motor case. At least one of the plurality of flow passages fluidly connects the radial portion and the axial portion.

A turbo compressor comprises a rotary shaft including a rotor; a first impeller coupled to one side of the rotary shaft, a thrust bearing runner coupled between the first impeller and the rotary shaft, an impeller sleeve compressed and coupled between the first impeller and the thrust bearing runner, a second impeller coupled to the other side of the rotary shaft, and a tie rod passing through the first impeller and a thrust bearing and fastened to the rotary shaft.

The invention relates to a compressor machine (10; 10a), in particular a generator or a compressor unit for compressing a gas, comprising a shaft (12) which is arranged in a housing (18) so as to be able to rotate about a longitudinal axis (11) and which is mounted in at least two radial bearings (20, 22) and a thrust bearing (24), the radial bearings (20, 22) and/or the thrust bearing (24) being in the form of an aerodynamic or aerostatic bearing, the shaft (12) being at least indirectly connected to a compressor stage (15) or driving stage comprising an impeller wheel (13).

A radial blower, in particular for a cooling machine, comprising a housing in which a shaft is rotationally mounted, which receives at least one impeller wheel of a compressor at one end, which is secured to the housing, comprising at least one radial bearing and at least one axial bearing via which the shaft is rotationally mounted in the housing, and comprising a motor driven by a rotor and a stator and provided between the first and the second radial bearing, wherein at least one channel having a pressure connection for a pressure medium to be supplied is provided in the housing, which channel feeds into a rotor space formed between the shaft and the housing and extending from the impeller wheel to the radial bearing or axial bearing, which is provided next to the impeller wheel.

A bearing includes a thrust gas bearing attached to a journal bearing and two or more converging-diverging orifices defined in a surface of at least one of the thrust gas bearing and the journal bearing. The converging-diverging orifices supply at least one pressurized gas to an interior of the bearing. Hydrodynamic lifting grooves are provided on the faces of the thrust gas bearing and the journal bearing and provide improved load capacity and sealing capabilities. Control over the ratios of the pressurized gases provides for additional sealing capabilities and reduced leakage. A metal mesh damper provides increased damping of the gas bearing.

A small gas turbine engine with a ceramic turbine to allow for higher turbine inlet temperatures, where a metallic compressor is secured to a ceramic shaft extending from a ceramic turbine to form a single piece ceramic shaft and turbine, where a threaded nut secures a split ring retainer on the compressor end of the ceramic shaft. A hollow thrust runner is compressed between the compressor disk and the turbine disk by the threaded nut to secure rotor together. A centering spring forms a tight fit between the metallic thrust runner and the ceramic shaft on the turbine side.

A centrifugal compressor is provided. The centrifugal compressor includes a housing and a rotatable assembly mounted for rotation about an axis within the housing. The rotatable assembly includes an impeller forming part of a compressor stage. A first air intake is located at a first end of the apparatus, the first air intake providing an air source for the compressor stage and a second air intake is located at a second end of the apparatus. A thrust plate is attached to the rotatable assembly, the thrust plate including at least one interior channel so that air entering the second air inlet passes through the at least one interior channel.

A turbo compressor includes a driving unit including a stator and a rotor that are configured to generate a rotational force and a rotary shaft that is connected to and rotated by the rotor, an impeller connected to the rotary shaft to pressurize a suction refrigerant in the radial direction of the rotary shaft and a casing that receives the driving unit and the impeller and supports the rotary shaft. The casing includes a first shell to which the stator is fixed and that rotatably supports the rotary shaft, and a second shell that is spaced apart from the first shell and surrounds the first shell. A shell passage is defined between the first and second shells. The discharged refrigerant cools the driving unit, which improves the efficiency of the compressor.

A turbo compressor assembly of a cooling machine has a shaft mounted in a common housing with first and second radial dynamic gas bearings and a thrust bearing. A supply stream of working gas supplied to the first radial bearing is formed between an inner wall of a compressor body and the shaft, and a supply stream of working gas from a turbo expander supplied to the second radial bearing and to the thrust bearing is formed between an inner wall of a turboexpander body and the shaft. The first radial dynamic gas bearing is sealed towards the electric motor rotor by a shaft seal. A surface in a shape of an annulus is formed on the shaft between the first radial bearing and the shaft seal, the annulus perpendicular to an axis of the shaft and functioning as a piston for balancing an axial force acting on the shaft.

A rotary machine for an aeronautical device includes a thrust generator. The rotary machine additionally includes a rotary component rotatable with the thrust generator. Moreover, the rotary machine of the present disclosure includes a plurality of gas bearings, with the plurality of gas bearings substantially completely supporting the rotary component of the rotary machine.