Gas turbine engines include a compressor section having an impeller configured to compress a core flow. A combustor section having a combustor is arranged downstream from the compressor section along a path of the core flow. A turbine section is arranged downstream from the combustor section along the path of the core flow, with the turbine section having a plurality of first vanes arranged at an outlet of the combustor and at least one first vane of the plurality of first vanes includes an internal vane path. The path of the core flow, in a flow direction, passes through the impeller of the compressor section, the internal vane path internal to the first vane, the combustor, and then between external surfaces of the plurality of first vanes to enter the turbine section.

The swirl flow ceiling fan has four major elements. They are: a cylindrical diffuser, an inducer, a stationary enclosure and a safety disc. As the fan rotates, the ambient air is drawn in at the centre. The air which was drawn in by the inducer further gets energised within an enclosed space. The air's velocity gets increased. The charged air is pushed into the numerous spiral compartments of the revolving cylindrical diffuser. Then, finally, the cylindrical diffuser delivers the energised air in to the space. All the features collectively provide a very efficient swirl flow of the air with lesser noise levels and better comfort. It is also found to be cost-effective in its working as well in its manufacturing.

The invention relates to a ventilator wheel which is produced in the form of a radial or a diagonal ventilator wheel, and comprises a bottom disc and a plurality of ventilator blades arranged, on said bottom disc, so as to be distributed about an axial rotational axis, said bottom disc comprising a circumferential radial outer edge section that, when viewed in cross-section, extends in a curved shape in at least some sections and thus forms an elliptical transition of said bottom disc from a radial extension into an axial extension.

A hybrid drive engine uses air foil shaped disks of a first configuration for a compressor portion thereof and air foil shaped disks of a second configuration for a turbine portion thereof, whereby the disks exhibit aerodynamic effects of lift. Particularly, the compressor disks are configured to cause aerodynamic lift off of a periphery of the disks, while the turbine disks are configured to cause aerodynamic lift off of an inner hole of the disks. The aerodynamic nature of the disks cause each disk thereof to form two opposing airfoil shapes either head to head or trailing edge to trailing edge across the through hole.

An impeller of a centrifugal compressor, the impeller including a web and blades secured to the web on a front face of the web. A point of intersection between a trailing edge and a blade root is at least one half-thickness of the web further forward than the blade root at an intermediate diameter of the impeller, and a point of intersection between the trailing edge and the blade tip is also further forward than the blade tip at an intermediate diameter of the impeller.

An isothermal turbo-compressor-condenser-expander arrangement includes heat-transferring blades that are mounted on, or surround, individual conduits. In operation, the open framework rotates in free air to promote heat exchange. The assembly includes a first plurality of spokes extending radially outwardly from a first central hub to an outer perimeter with first radial conduits that transport refrigerant under centrifugal force and compression from the hub to the outer perimeter. The first radial conduits include heat exchanging blades. A second plurality of spokes extend radially outwardly from a second central hub that each includes a second thermally-insulated conduit that transports refrigerant from the outer perimeter to the second central hub. Axial conduits extend axially at the outer perimeter. At least some of the axial conduits include an axial blade in thermal communication with the conduit.

Disclosed herein is a centrifugal fan. The centrifugal fan includes a back plate having a central portion for coupling with a rotation center shaft, a plurality of blades extending from the back plate, and a shroud which is connected to end portions of the blades and has an introduction end portion and a discharge end portion through which fluid passes, and the discharge end portion is rounded with a predetermined curvature in a direction away from the back plate.

A turbomachine, includes a case and a rotor positioned in the case so that it can rotate with respect to the case around its own longitudinal axis. The rotor includes: one blading located on the rotor and disposed in a respective transit volume bounded between the rotor and the case for the passage of a first working fluid; one helical conduit developing in loops around the longitudinal axis and extending between one inlet and one outlet for the passage of a second working fluid. The helical conduit is radially internal with respect to the blading has loops with gradually increasing or decreasing radial dimensions from the inlet towards the outlet.

In this pump apparatus, each of plural gate marks formed in a second blade member is formed at an intermediate position in a circumferential direction of a rotor between two blades that are adjacent to each other in the circumferential direction of the rotor, and the even number of blades are disposed between the gate marks in the circumferential direction of the rotor. The plural gate marks are disposed on an outer side, in the radial direction of the rotor, of an outer circumferential surface of a portion, which is connected to the second blade member, in a magnet holding member formed in a tubular shape.