An alternator, such as for use in an electrostatic spray gun, comprises an electromagnetic alternator, a housing and an impeller. The electromagnetic alternator has a shaft. The electromagnetic alternator is disposed within the housing. The housing has an air aperture. The impeller is mounted to the shaft within the housing so as to be aligned with the air aperture. The impeller includes blades having curved leading and trailing edges. In one embodiment, each blade has a curvature so as to be perpendicular to the air aperture across an entire arc over which each impeller blade has a line of sight of the air aperture.

In a radial turbine nozzle and its assembling method, a first flange member of a first divided annular portion is inserted into a first outer side groove of a first ring. A second flange member of a second divided annular portion is inserted into a second outer side groove of a second ring. A plurality of segments are connected together in a circumferential direction, by overlapping first divided surfaces of two of the segments that are adjacent in a circumferential direction of a radial turbine, and overlapping second divided surfaces of the two of the segments.

In a radial turbine nozzle and its assembling method, a first flange member of a first divided annular portion is inserted into a first outer side groove of a first ring. A second flange member of a second divided annular portion is inserted into a second outer side groove of a second ring. A plurality of segments are connected together in a circumferential direction, by overlapping first divided surfaces of two of the segments that are adjacent in a circumferential direction of a radial turbine, and overlapping second divided surfaces of the two of the segments.

A disc turbine engine with a multi disc engine where each disc engine includes a turbine blade, a low-pressure compressor blade, a high-pressure compressor blade, and a bearing. Each disc engine runs freely and individually, counter-rotating directions from each other and around a fixed shaft. Each disc engine has its own cooling system. The compressor's blades act as cooling fins for the turbine blade. A coolant, such as liquid hydrogen is used to fill the hollow body of the high-pressure compressor, the hollow body of the lower pressure compressor, and the hollow body of the turbine blade with a connection chamber in between the hollow blades as a sealed system. The nozzle is filled with a coolant inside the hollow bodies of the nozzle and guide fan as a sealed system.

A turbine engine is provided that includes a first rotor, a second rotor and a combustor section. The first rotor includes a first set of compressor blades. The second rotor is adjacent the first rotor. The second rotor includes a second set of compressor blades and a set of turbine blades respectively connected to the second set of compressor blades. The combustor section is configured to receive air compressed by the first and the second sets of compressor blades. The combustor section is also configured to provide combustion products to the set of turbine blades.

A turbine engine is provided that includes a first rotor, a second rotor and a combustor section. The first rotor includes a first set of compressor blades. The second rotor is adjacent the first rotor. The second rotor includes a second set of compressor blades and a set of turbine blades respectively connected to the second set of compressor blades. The combustor section is configured to receive air compressed by the first and the second sets of compressor blades. The combustor section is also configured to provide combustion products to the set of turbine blades.

A disc turbine engine includes a multi disc engine in which each disc engine includes a turbine blade, and low-pressure compressor blade, a high-pressure compressor blade and a bearing that runs the disc engine freely around a shaft. Each disc engine has its own cooling system, the compressor's blades act as cooling fins for the turbine blade, and air bleeding from the high-pressure compressor to the lower pressure compressor through a hollow turbine blade. Cooling the nozzle is by attaching the nozzle to the guide fan and by air bleeding through the hollow body. There is no stator in between the disc engine and no large shaft is required because the power produced by each turbine blade is consumed by its own compressor. The weight and cost of this engine will be less than other engines at the same thrust output.

A rotor assembly for a centrifugal pump includes a rotor and a rotor cover, defining a fluid chamber therebetween, and having openings or channels that are provided in either the rotor cover or the rotor, or both, to direct fluid from the fluid chamber into the rotor or rotor cover of the rotor assembly to provide reduction of increased pressure that is experienced within the fluid chamber, especially at or near the center of the fluid chamber.

An alternator, such as for use in an electrostatic spray gun, comprises an electromagnetic alternator, a housing and an impeller. The electromagnetic alternator has a shaft. The electromagnetic alternator is disposed within the housing. The housing has an air aperture. The impeller is mounted to the shaft within the housing so as to be aligned with the air aperture. The impeller includes blades having curved leading and trailing edges. In one embodiment, each blade has a curvature so as to be perpendicular to the air aperture across an entire arc over which each impeller blade has a line of sight of the air aperture.

A gas system has a first compressor stage for compressing a process gas. The first compressor stage includes an intake side and a pressure side. A seal gas is provided outside the first compressor stage in order to prevent process gas from issuing from leaks in the first compressor stage, having at least one second line for returning a gas mixture issuing from the gas system, this mixture including at least of process gas and seal gas. The at least one second line is configured for returning the issuing gas mixture to the intake side of the first compressor stage and/or to a location in the gas system upstream of the first compressor stage.