An internal combustion engine, ICE, system, includes a turbocharger having a turbine and a compressor for compressing intake air and feeding the intake air to the ICE. A turbo turbine unit is disposed in an exhaust gas path downstream the turbocharger to receive exhaust gas from the turbocharger. The turbo turbine unit having a turbine wheel, a bearing housing defining an inside volume for containing lubrication oil, and a sealing arrangement positioned in the vicinity of the turbine wheel for preventing lubrication oil from escaping from the inside volume of the bearing housing to an exhaust duct of the turbo turbine unit. A buffer air conduit extends between a selected position at the compressor and a buffer air inlet of the turbo turbine unit. The buffer air inlet is in fluid communication with a buffer air channel inside the turbo turbine unit to direct buffer air to a position in-between axially opposite arranged annular sealing members to provide a counter-pressure against at least one of the annular sealing members.

A gas turbine engine includes a fan section that includes a fan with fan blades. The fan section drives air along a bypass flow path in a bypass duct. A gear reduction is in driving engagement with the fan and has a gear reduction ratio of greater than 3.0 and less than 4.0. A low spool includes a low pressure turbine that drives a low pressure compressor and drives the gear reduction to drive the fan at a speed slower than the low pressure turbine. The low pressure compressor includes a greater number of stages than the low pressure turbine. A high spool includes a high pressure turbine that drives a high pressure compressor. The high pressure compressor is a nine stage high pressure compressor and includes a pressure ratio per stage of greater than or equal to 1.20 and less than or equal to 1.33.

A gas turbine engine includes a fan section that includes a fan with fan blades. The fan section drives air along a bypass flow path in a bypass duct. A gear reduction is in driving engagement with the fan and has a gear reduction ratio of greater than 3.0 and less than 4.0. A low spool includes a low pressure turbine that drives a low pressure compressor and drives the gear reduction to drive the fan at a speed slower than the low pressure turbine. The low pressure compressor includes a greater number of stages than the low pressure turbine. A high spool includes a high pressure turbine that drives a high pressure compressor. The high pressure compressor is a nine stage high pressure compressor and includes a pressure ratio per stage of greater than or equal to 1.20 and less than or equal to 1.33.

An aero-propulsion system includes a drive shaft, a low-pressure compressor, a fan shaft driving a fan, a reduction device that couples the drive shaft and the fan shaft, and an inlet channel which extends between the fan and the low-pressure compressor, the inlet having a predetermined mean radius, a ratio between a mean radius of the inlet channel and the mean radius of the low-pressure compressor, on the one hand, and the reduction ratio of the reduction mechanism, on the other hand, being less than 0.35.

A magnetic coupling assembly includes a rotatable male coupling member, a rotatable female coupling member, a static separation member, a first channel, a second channel, a third channel, and a magnetic coupling section of the static separation member, wherein the magnetic coupling section is a section of the static separation member. The rotatable female coupling member and the rotatable male coupling member are rotatably coupled by magnets through the magnetic coupling section. The first channel, the second channel, and the third channel contain fluid forced to flow through the first, second, and third channels for cooling and rotodynamic stabilization.

A vapor recovery turbo compressor is provided for recovering low pressure hydrocarbon vapors from tanks, oil or gas wells or other low-pressure sources. The vapor recovery turbo compressor includes a turbo expander that receives high pressure hydrocarbon gas that drives the turbo expander. The turbo expander drives a vapor recovery compressor. The vapor recovery compressor receives very low-pressure hydrocarbon gas from tanks and other sources and generates medium pressure hydrocarbon gas that can be used for various purposes.

The present invention is directed to a fluid sealing member and a motor for preventing or reducing chances of fluids and/or substances or products from entering the motor chamber or cavity of a motor and causing damage to the motor's internal components and/or causing the motor to make undesirable noises or sounds. The present invention is also directed to a motor having a fluid sealing member, and to a fluid pump having a fluid sealing member. The present invention is further directed to a fluid pump that comprises a jet assembly and a motor assembly, which comprises a motor. The fluid pump may further comprise one, some or all of the following: a fluid sealing member, a mounting housing member or coupling device, a gasket or seal, a liner (when a liner is not already provided or present), and a driven magnetic disc assembly having a magnetic pole array.

A turbo compressor includes a housing with a refrigerant suction hole, through which a refrigerant is introduced, at a front portion thereof, and a motor case defining an accommodation space. The accommodation space includes a rotation shaft extending in a front-rear direction and a motor that is configured to rotate the rotation shaft. A first impeller is coupled to one end of the rotation shaft and a second impeller is coupled to the other end of the rotation shaft. The first impeller is configured to primarily compress the refrigerant introduced into the refrigerant suction hole. A connection passage, that surrounds the motor case extends backward from an outlet of the first impeller. The second impeller is configured to secondarily compress the refrigerant introduced through the connection passage.

A turbo compressor includes a housing with a refrigerant suction hole, through which a refrigerant is introduced, at a front portion thereof, and a motor case defining an accommodation space. The accommodation space includes a rotation shaft extending in a front-rear direction and a motor that is configured to rotate the rotation shaft. A first impeller is coupled to one end of the rotation shaft and a second impeller is coupled to the other end of the rotation shaft. The first impeller is configured to primarily compress the refrigerant introduced into the refrigerant suction hole. A connection passage, that surrounds the motor case extends backward from an outlet of the first impeller. The second impeller is configured to secondarily compress the refrigerant introduced through the connection passage.

Potentially off-grid grain conditioners that can be operably connected to an aeration grain bin or silo to blow heated air through the crop to dry the crop or to blow ambient temperature air through the crop to cool it are disclosed. A fan is powered by a motor that may be mounted inside the air stream to allow the heat from the motor to be collected and forced into the airstream that is blown into the grain bin. The engine exhaust may be routed through an air exchanger to remove heat from the exhaust and direct heat into the grain bin, or the exhaust may be put into the atmosphere without capturing any of the heat, which allows the fan to operate in a cooling mode. The motor may be mounted inline or mounted to the side for a centrifugal aeration fan.