A cooling system that may include a source of liquid natural refrigerant, a heat exchanger in communication with the source of liquid natural refrigerant that is configured to convert the liquid natural refrigerant into a gaseous natural refrigerant, a compressor in communication with the heat exchanger and configured to increase a temperature and pressure of the gaseous natural refrigerant received from the heat exchanger, and an exhaust device in communication with the compressor and configured to expel the gaseous natural refrigerant received from the compressor to air of an external ambient environment. The exhaust device includes a membrane that permits the gaseous natural refrigerant to exit the exhaust device while preventing or at least minimizing the air of the external ambient environment from entering the exhaust device.

Disclosed is a two-stage gas compressing apparatus with a compressed-gas pressure-difference-use optimizing cooling unit to perform cooling using a pressure difference, and more specifically, to a two-stage gas compressing apparatus with a compressed-gas pressure-difference-use optimizing cooling unit to perform cooling using a pressure difference, the compressed-gas pressure-difference-use optimizing cooling unit cooling an inside of the two-stage gas compressing apparatus, collecting a gas used in cooling, re-compressing collected gas, and supplying a compressed gas to a portion which uses the compressed gas by using the pressure difference between gases generated in the completely airtight two-stage gas compressing apparatus so as to promote maximization of energy efficiency and a virtuous circle of energy.

The integrated expander and motor-compressor assembly comprises a compression section mounted between the two radial bearings on a trans-mission shaft, an expander cantilevered at a free end of the transmission shaft, a gas diffuser and a duct between the expander and a first radial bearing, the first radial bearing been the closest radial bearing to the expander. The gas diffuser diffuses a gas barrier which is sucked up by the duct.

The impeller of a rotating machine according to at least one embodiment of the present discloser is provided with: a disc; a cover disposed on an opposite side of a radial passage from the disc in an axial direction; and a blade disposed between the disc and the cover. In a dimensionless position along a camber line of the blade when the position of a leading edge of the blade is defined as 0 and the position of a trailing edge of the blade is defined as 1, a position where an angle difference between a first blade angle at a disc-side end portion of the blade and a second blade angle at a cover-side end portion of the blade is maximum is in a range of 0.5 or more and 1 or less. The first blade angle is −10 degrees or more and 0 degrees or less at the position where the angle difference is maximum.

A centrifugal compressor bundle that is provided with a bundle main body in which is formed an annular intake flow channel (FC1) that is centered on an axis line (O) and that leads a process gas (G) into a flow channel (FC) of an impeller, and in which is also formed an annular discharge flow channel (FC2) that is centered on the axis line (O) and that discharges the process gas (G) from the flow channel (FC) of the impeller. The bundle main body has a plurality of diaphragms that are aligned in the direction of the axis line (O) and that are bonded to each other. From among the plurality of diaphragms, an intake diaphragm in which the intake flow channel (FC1) is formed is partitioned so as to have an upper-half part and a lower-half part that sandwich, from above and below, a horizontal plane that includes the axis line (O). The upper-half part and the lower-half part have the same rigidity in the direction of the axis line (O).

A suspending tool includes a suspending tool main body that extends to be parallel with an axial direction above a rotor main body, a pair of bearing supporting portions that are disposed at an interval in the axial direction and are detachable from the bearing portions, a pair of seal supporting portions that are disposed inside the pair of bearing supporting portions in the axial direction at an interval in the axial direction and are detachable from the seal portions, and a plurality of diaphragm supporting portions that are disposed inside the pair of seal supporting portions in the axial direction such that the diaphragm supporting portions are disposed at intervals in the axial direction and are detachable from the diaphragms.

A rotary machine includes a compression section that is disposed between the pair of radial bearings in a casing and compresses a fluid, an expansion section that is disposed side by side with the compression section and expands the fluid, and a thrust bearing that is disposed at a position close to a first end portion or a second end portion of a rotary shaft in an axial direction with respect to the compression section and the expansion section. Among a compression section suction port, a compression section discharge port, an expansion section suction port, and an expansion section discharge port, the compression section suction port is disposed at a position closest to the first end portion in the axial direction, and the expansion section discharge port is disposed at a position closest to the second end portion in the axial direction.

A arranged in the casing and configured to rotate around a vertical rotation axis. The rotor comprises at least one impeller having an impeller suction side and an impeller delivery side. The compressor includes a gas inlet and a gas outlet, as well as a gas flow path extending from the gas inlet to the gas outlet. An inlet plenum extends from the gas inlet towards the impeller suction side. At least one suction tube having a lower suction end and an upper discharge end is arranged such that the lower suction end thereof is arranged at a bottom of the inlet plenum. The suction tube extends upwardly towards the impeller suction side.

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.

A turbo-machine arrangement having a compressor section comprising a compressor shaft, an electric machine having a shaft, the compressor shaft is coaxial to the shaft. The compressor shaft is coupled to the electric machine shaft. The electric machine and compressor section are arranged in a common housing and mounted via bearings. The housing having a supply line via which uncompressed working medium is supplied, a discharge line, via which compressed working medium is discharged, and an ejector, supplied via a first connection with working medium at a first pressure level for drawing in working medium at a lower second pressure level via a second connection. A mixture formed in the ejector is supplied to the electric machine and/or another assembly to be cooled via a third connection.