The present invention relates to a guide vane, in particular an outlet guide vane and/or a guide vane for a compressor stage of a gas turbine, wherein the vane has a vane blade with a first vane blade portion and a second vane blade portion, and the first vane blade portion can be reversibly rotated in relation to the second vane blade portion about an axis of rotation from a first position to a second position, wherein, in at least one profile portion of the vane blade, the axis of rotation is arranged outside of a profile of the first vane blade portion, and/or a profile of the first vane blade portion has a suction side with a first contour portion and a second contour portion, which, in particular, is adjoined thereto, and a profile of the second vane blade portion has a pressure-side contour portion.

A pump assembly includes multiple impeller stages, each impeller stage including at least one impeller vane. At least one impeller stage includes at least one impeller vane with at least one perforation disposed therethrough.

An axial fan wheel, in particular for the radiator of a motor vehicle engine, is described. The axial fan wheel includes a crown ring having a multiplicity of rotor blades, a hub having an inner ring which is connected or connectable to a drive shaft, and having, for the purpose of torque transmission, connection surfaces along an outer periphery of the hub which are connected to the inner ring and to the crown ring. The hub has through-passages between the inner ring and the outer periphery. At least one element, arranged rotationally fixedly on the axial fan wheel inside the crown ring, is designed to maintain a pressure difference in the axial direction when the axial fan wheel rotates.

The invention relates to a recirculation device for a gas of a process device, said recirculation device comprising a recirculation pump, wherein the recirculation pump is a side channel pump.

A rotor for an aircraft engine includes a hub having a rotation axis, a circumferential array of structural members extending radially outward from the hub to an annular ring, the structural members having cross-sections that increase in length as the structural members extend from the hub to the annular ring, the length of each cross-section of the cross-sections defined by opposite edges of a structural member of the structural members that corresponds to that cross-section, and a circumferential array of airfoils extending radially outward from the annular ring.

An axial fan wheel, in particular for the radiator of a motor vehicle engine, is described. The axial fan wheel includes a crown ring having a multiplicity of rotor blades, a hub having an inner ring which is connected or connectable to a drive shaft, and having, for the purpose of torque transmission, connection surfaces along an outer periphery of the hub which are connected to the inner ring and to the crown ring. The hub has through-passages between the inner ring and the outer periphery. At least one element, arranged rotationally fixedly on the axial fan wheel inside the crown ring, is designed to maintain a pressure difference in the axial direction when the axial fan wheel rotates.

A rotor for an aircraft engine includes a hub having a rotation axis, a circumferential array of structural members extending radially outward from the hub to an annular ring, the structural members having cross-sections that increase in length as the structural members extend from the hub to the annular ring, the length of each cross-section of the cross-sections defined by opposite edges of a structural member of the structural members that corresponds to that cross-section, and a circumferential array of airfoils extending radially outward from the annular ring.

The invention relates to a vacuum system, comprising a vacuum pump, preferably turbomolecular pump, and at least one vacuum chamber, wherein the vacuum pump comprises: at least a first and a second inlet and a common outlet; at least a first and a second pumping stage, each pumping stage comprising at least one rotor element being arranged on a common rotor shaft, wherein the first inlet is connected to an upstream end of the first pumping stage and the second inlet is connected to an upstream end of the second pumping stage; a direction element for preventing a gas flow from a downstream end of the first pumping stage to the second inlet; a conduit having a conduit inlet and a conduit outlet, wherein the conduit inlet is connected to the downstream end of the first pumping stage and the conduit outlet is connected to a location downstream of the second pumping stage; wherein the first inlet and the second inlet of the pump are connected to the same vacuum chamber.

The present invention is an electric propulsion motor that can be used to propel air, land, and sea vehicles consisting of a gyroscope's flywheel that has been split into two counter rotating sections, perimeter and hub, each section containing spokes that are shaped to produce thrust when rotated, a stator with individually controlled field coils located on its inside and outside diameters, permanent magnets integrated into the flywheel sections proximate to the stator's field coils, and a bearing system to support each flywheel section. The invention is self-contained needing no external propulsion or drive means, self-stabilizing due to the gyroscopic forces created by its spinning hub and perimeter flywheels, thrust producing because of the shape of the spokes of the two flywheels, and rotational torque cancelling with counter rotating flywheel sections. A Chimara Effect is created that both stabilizes and propels the vehicle.

A system includes a machine; a centrifugal fan, the centrifugal fan having a plurality of centrifugal fan blades and being constructed to generate a cooling airflow for cooling the machine; and an axial flow inducer disposed on the plurality of centrifugal fan blades, wherein the axial flow inducer is constructed generate an axial flow through a central portion of the centrifugal fan.