Abstract: A suction pipe 200 of a centrifugal compressor 20, the centrifugal compressor 20 having a suction port 22 that is open to direct the working fluid to an impeller 21, the suction pipe 200 including a first opening portion 31 to be directly or indirectly connected to the suction port 22 and a second opening portion 32 positioned upstream from the first opening portion 31 in the flow direction of the working fluid. The second opening portion 32 is positioned below the first opening portion 31 in the vertical direction. The first opening portion 31 and the second opening portion 32 are open toward the same direction.

Abstract: A rotary machine 100 includes a bearing 10, a rotary shaft 20, a turbine wheel 30, a turbine nozzle 31, and a first cavity 40. The bearing 10 has a first end face 10a and a second end face 10b each positioned in the axial direction of the rotary shaft 20. The distance from the first end face 10a to the turbine wheel 30 is shorter than the distance from the second end face 10b to the turbine wheel 30. The first cavity 40 is positioned, in the axial direction of the rotary shaft 20, between a back surface 31b of the turbine nozzle 31 and the second end face 10b of the bearing 10 or between the back surface 31b of the turbine nozzle 31 and a space 11 that the second end face 10b of the bearing 10 faces. The first cavity 40 is present in the zone overlapping with the turbine nozzle 31 in a radial direction of the rotary shaft 20.

Abstract: A bearing structure (100) of the present disclosure includes: a rotating shaft (11); a dynamic bearing (12) including a foil (22) and a foil holder (21), the foil (22) being disposed around the rotating shaft (11) to constitute a bearing surface, the foil holder (21) holding the foil (22); a bearing support member (13) disposed around the dynamic bearing (12) to support the dynamic bearing (12); and at least one elastic body (14) disposed between the bearing support member (13) and the foil holder (21).

Abstract: A rotating machine (100) of the present disclosure includes: a bearing (10); a rotating shaft (20) having a hollow portion (21) included in a portion (20s) supported by the bearing (10); a fluid element (30) attached to one end portion of the rotating shaft (20); an introduction hole (22) that is provided, in the rotating shaft (20), on a back side of the fluid element (30), and that directs a working fluid to the hollow portion (21); and a discharge hole (23) that is provided, in the rotating shaft (20), at a position distant from the introduction hole (22) beyond the portion (20s) supported by the bearing (10), and that directs the working fluid to an outside of the hollow portion (21).

Abstract: A bearing structure includes a rotating shaft, a thrust collar, and a first thrust bearing. The rotating shaft has a central axis. The thrust collar is mounted on the rotating shaft. The first thrust bearing includes a first dynamic pressure generating mechanism. The first dynamic pressure generating mechanism faces the thrust collar. The relation Rt>Rf1 is satisfied, where Rt represents a length from the central axis to the outer circumferential edge of the thrust collar, and Rf1 represents a length from the central axis to the outer circumferential edge of the first dynamic pressure generating mechanism.

Abstract: A first thrust bearing includes a first electromagnet and a first member. A second thrust bearing includes a second electromagnet and a second member. A magnetic force generated by the first electromagnet and the second electromagnet, and dynamic gas pressure generated by the first member and the second member due to rotation of a rotating shaft support an axial load of the rotating shaft.

Abstract: A disclosed micro gas turbine system includes a micro gas turbine apparatus and an extracting cycle apparatus. The micro gas turbine apparatus includes a first compressor, a burner, and a first turbine. The first turbine expands a combustion gas generated by the burner. The extracting cycle apparatus includes a second compressor and a second turbine. The second compressor receives a flow of extracted air that is generated by extracting a part of a working fluid discharged from the first compressor. The second turbine expands the working fluid discharged from the second compressor. The working fluid discharged from the second turbine cools down the first turbine.

Abstract: A gas turbine rotor includes a first rotor and a second rotor. The first rotor includes a compressor impeller, a turbine wheel, and a shaft. The turbine wheel has a common rotational axis with the compressor impeller. The shaft connects the compressor impeller to the turbine wheel. The second rotor is an electric generator rotor and defines an inner hollow space. The shaft includes an insertable portion disposed in the inner hollow space of the second rotor.

Abstract: A turbine nozzle according to the disclosure is a turbine nozzle that is used in a radial turbine and includes a ring-shaped hub, a plurality of nozzle vanes that are arranged at equal angular intervals on the hub, and a flow path that is formed between the nozzle vanes. The flow path includes a throat that has a smallest flow path cross-sectional area with respect to a flow direction of working fluid. On a downstream side of the throat with respect to the flow direction, the flow path cross-sectional area increases. Heights of the nozzle vanes on the downstream side of the throat with respect to the flow direction are greater than heights of the nozzle vanes in the throat and gradually increase from an upstream side toward the downstream side with respect to the flow direction.

Abstract: A turbo machine of the present disclosure includes a rotation shaft, a first bearing, a casing, an impeller, a first space, a second space, a storage tank, a first outlet passage, a supply passage, a pump, a main passage, and a sub-passage. The second space is in communication with a space formed between a bearing surface of the first bearing and an outer surface of the rotation shaft. The main passage is in communication with the second space and extends in the rotation shaft from an end of the rotation shaft in an axial direction of the rotation shaft. The sub-passage is formed in the rotation shaft and allows communication between the space between the bearing surface of the first bearing and the outer surface of the rotation shaft and the main passage.

Abstract: A turbo machine of the present disclosure includes a cylindrical bearing housing, a rotation shaft, a bearing, a bearing holder, and an end elastic body. The rotation shaft is located in the bearing housing. The bearing rotatably supports the rotation shaft at least in a radial direction of the rotation shaft. The bearing holder faces one end of the bearing and is fixed to the bearing housing. The end elastic body is disposed between the one end of the bearing and the bearing holder in the axial direction of the bearing and is in contact with the bearing and the bearing holder. The end elastic body is formed of a material having a lower modulus of elasticity than a material forming the bearing holder.

Abstract: A refrigeration apparatus includes a container such as an evaporator for holding refrigerant, and a compressor for compressing refrigerant vapor. The compressed vapor is returned to the container, and stored as liquid. The liquid refrigerant is withdrawn from the container and then returned to the container via a first path through a heat exchanger for cooling a space, or a second path that does not pass through the heat exchanger. Upon returning to the container, the liquid refrigerant is at least partly evaporated due to the reduced pressure in the container caused by the operation of the compressor, and the container is cooled by the latent heat of evaporation. Thus, the container can act as a cold storage unit. The cold storage effect is increased when the refrigerant is returned to the container via the second path.

Abstract: A gas turbine apparatus includes a first compressor, a combustor, and a first turbine. The first compressor compresses a working fluid. The combustor injects a fuel into the working fluid discharged from the first compressor and combusts the fuel. The first turbine expands combustion gas produced in the combustor. A bleeding cycle apparatus includes a second compressor and an expansion mechanism. The second compressor compresses the working fluid, extracted from the gas turbine apparatus, whose pressure has been raised by the first compressor. The expansion mechanism expands the working fluid discharged from the second compressor. A first heat exchanger performs a heat exchange between the working fluid compressed by the first compressor and to be expanded by the first turbine and the working fluid compressed by the second compressor and to be expanded by the expansion mechanism.

Abstract: A turbo machine according to present disclosure includes a rotating shaft, a first impeller, a first fluid bearing, a first holding member, a first lubricating liquid casing, a first supplying passage, and a first squeeze film damper. The first fluid bearing rotatably supports the first taper portion and the first cylindrical portion. The first fluid bearing is attached to the first holding member. The first lubricating liquid casing forms a first storing space. The first supplying passage is a passage through which a lubricating liquid is supplied to the first storing space. The first squeeze film damper is a space located between the first fluid bearing and the first holding member. The first squeeze film damper communicates with the first supplying passage.

Abstract: A flow distributor changes a ratio between a flow rate of a working fluid flowing from an inlet to a first outlet and a flow rate of the working fluid flowing from the inlet to a second outlet. Into the inlet, the working fluid that is boosted by a first compressor and that is extracted from a gas turbine apparatus flows. A second compressor compresses the working fluid flowing from the first outlet. A first cooler cools the working fluid discharged from the second compressor. The first cooler cools the working fluid flowing from the second outlet to bypass the second compressor. A second expansion turbine expands the working fluid flowing from the first cooler.

Abstract: A gas turbine system (1A) includes a gas turbine unit (2) and a cooling fluid generator (5). The gas turbine unit (2) includes a first compressor (21) and a first expansion turbine (23) coupled to each other by a first shaft (22), a combustor (26), and a fuel tank (30). A fuel held in the fuel tank (30) circulates through a fuel circulation passage (31). A working fluid that has a pressure increased by the first compressor (1) is extracted from the gas turbine unit (2). The cooling fluid generator (5) includes a cooler (55) for cooling, with the fuel flowing through the fuel circulation passage (31), the working fluid that has been extracted from the gas turbine unit (2), and a second expansion turbine (53) for expanding the working fluid that has flowed out of the cooler (55).

Abstract: A first thrust bearing includes a first electromagnet and a first member. A second thrust bearing includes a second electromagnet and a second member. A magnetic force generated by the first electromagnet and the second electromagnet, and dynamic gas pressure generated by the first member and the second member due to rotation of a rotating shaft support an axial load of the rotating shaft.

Abstract: A gas turbine rotor includes a first rotor and a second rotor. The first rotor includes a compressor impeller, a turbine wheel, and a shaft. The turbine wheel has a common rotational axis with the compressor impellor. The shaft connects the compressor impeller to the turbine wheel. The second rotor is an electric generator rotor and defines an inner hollow space. The shaft includes an insertable portion disposed in the inner hollow space of the second rotor.

Abstract: A turbo machine according to the present disclosure includes a rotating shaft, an impeller, a first bearing, and a first supply passage. The rotating shaft includes a first taper portion and a first cylindrical portion. The first bearing includes a first taper support surface and a first cylindrical portion support surface, the first taper support surface including a first taper hole forming surface and rotatably supporting the first taper portion, the first cylindrical portion support surface rotatably supporting the first cylindrical portion. The first supply passage is open to a space formed between the first cylindrical portion and first cylindrical portion support surface. An inclination angle of the first taper hole forming surface with respect to the axial direction of the first bearing is greater than an inclination angle of an outer surface of the first taper portion with respect to the axial direction of the rotating shaft.

Abstract: A turbine nozzle according to the disclosure is a turbine nozzle that is used in a radial turbine and includes a ring-shaped hub, a plurality of nozzle vanes that are arranged at equal angular intervals on the hub, and a flow path that is formed between the nozzle vanes. The flow path includes a throat that has a smallest flow path cross-sectional area with respect to a flow direction of working fluid. On a downstream side of the throat with respect to the flow direction, the flow path cross-sectional area increases. Heights of the nozzle vanes on the downstream side of the throat with respect to the flow direction are greater than heights of the nozzle vanes in the throat and gradually increase from an upstream side toward the downstream side with respect to the flow direction.