A hybrid jet engine, including a front cowling having a tubular shape, a rear cowling having a tubular shape and connected to the front cowling, a central core disposed within the front cowling and the rear cowling, a shaft disposed longitudinally within the central core, a plurality of main fan blades disposed at a first end of the shaft at the front cowling, a plurality of auxiliary fan blades disposed at a second end of the shaft at the rear cowling, at least one aerodynamic stabilizer disposed on a surface of the central core to extend therefrom, and at least one Tesla one way valve disposed on the surface of the central core to receive the ram air and to provide the ram air to the plurality of auxiliary fan blades.

A rotary manifold for a rotor assembly of a cohesion-type drive includes a manifold body extending along a drive axis for rotation thereabout, a first ductwork internal the body for fluid communication with a plurality of first chambers of the drive, and a second ductwork internal the body for fluid communication with a plurality of second chambers of the drive. The second ductwork is in fluid isolation of the first ductwork.

A rotary manifold for a rotor assembly of a cohesion-type drive includes a manifold body extending along a drive axis for rotation thereabout, a first ductwork internal the body for fluid communication with a plurality of first chambers of the drive, and a second ductwork internal the body for fluid communication with a plurality of second chambers of the drive. The second ductwork is in fluid isolation of the first ductwork.

A rotary manifold for a rotor assembly of a cohesion-type drive includes a manifold body extending along a drive axis for rotation thereabout, a first ductwork internal the body for fluid communication with a plurality of first chambers of the drive, and a second ductwork internal the body for fluid communication with a plurality of second chambers of the drive. The second ductwork is in fluid isolation of the first ductwork.

System for electrical energy generation from steam comprising at least one stage, each stage including: a steam-driven rotating toroidal ring; a housing comprising a toroidal cavity for containing the rotating toroidal ring, the housing further comprising at least one steam inlet, the housing further comprising a plurality of steam outlets for removing pressurized steam from the channels for at least a second portion of rotation of the rotating toroidal ring within the toroidal cavity; at least one bearing arrangement comprised by or attached to the housing within the toroidal cavity; and at least one pair of electrical coils, each electrical coil located on the outer surface of the housing at locations diagonally opposite from the other coil of each pair across the axis of the minor radius of the toroidal cavity and within the specific region where a time-varying magnetic field will occur as the rotating toroidal ring rotates.

System for electrical energy generation from steam comprising at least one stage, each stage including: a steam-driven rotating toroidal ring; a housing comprising a toroidal cavity for containing the rotating toroidal ring, the housing further comprising at least one steam inlet, the housing further comprising a plurality of steam outlets for removing pressurized steam from the channels for at least a second portion of rotation of the rotating toroidal ring within the toroidal cavity; at least one bearing arrangement comprised by or attached to the housing within the toroidal cavity; and at least one pair of electrical coils, each electrical coil located on the outer surface of the housing at locations diagonally opposite from the other coil of each pair across the axis of the minor radius of the toroidal cavity and within the specific region where a time-varying magnetic field will occur as the rotating toroidal ring rotates.

A hybrid jet engine, including a front cowling having a tubular shape, a rear cowling having a tubular shape and connected to the front cowling, such that the rear cowling is smaller than the front cowling, a central core disposed within the front cowling and the rear cowling, a shaft disposed longitudinally within the central core, a plurality of main fan blades disposed at a first end of the shaft at the front cowling, a plurality of auxiliary fan blades disposed at a second end of the shaft at the rear cowling, at least one aerodynamic stabilizer disposed on a surface of the central core to extend therefrom, to provide connected between the central core and the front cowling, and at least one modified Tesla one way valve disposed on the surface of the central core to receive the ram air and to provide the ram air to the plurality of auxiliary fan blades, such that the air is recycled through the shaft of the central core to power the plurality of main fan blades.

A hybrid jet engine, including a front cowling having a tubular shape, a rear cowling having a tubular shape and connected to the front cowling, such that the rear cowling is smaller than the front cowling, a central core disposed within the front cowling and the rear cowling, a shaft disposed longitudinally within the central core, a plurality of main fan blades disposed at a first end of the shaft at the front cowling, a plurality of auxiliary fan blades disposed at a second end of the shaft at the rear cowling, at least one aerodynamic stabilizer disposed on a surface of the central core to extend therefrom, to provide connected between the central core and the front cowling, and at least one modified Tesla one way valve disposed on the surface of the central core to receive the ram air and to provide the ram air to the plurality of auxiliary fan blades, such that the air is recycled through the shaft of the central core to power the plurality of main fan blades.

The purpose of the present invention is to minimize fluid leakage and pressure leakage, and a turbine apparatus of the present invention comprises: a turbine (510) rotating together with a turbine shaft (513) in response to an inflow of fluid; a turbine cover (520) coupled to an upper end of the turbine (510) to seal the turbine (510); a lower nozzle plate (350) and an upper nozzle plate (370) coupled to each other in the turbine (510); a plurality of nozzles (380) coupled between the lower nozzle plate (350) and the upper nozzle plate (370) to control the amount of fluid flowing into the turbine (510); a through pipe (356) coupled to the center of an upper surface of the lower nozzle plate (350) and passing through the lower nozzle plate (350) and the upper nozzle plate (370); and a control pipe (322) rotating inside the through pipe (356) for opening and closing the nozzles (380).

The purpose of the present invention is to minimize fluid leakage and pressure leakage, and a turbine apparatus of the present invention comprises: a turbine (510) rotating together with a turbine shaft (513) in response to an inflow of fluid; a turbine cover (520) coupled to an upper end of the turbine (510) to seal the turbine (510); a lower nozzle plate (350) and an upper nozzle plate (370) coupled to each other in the turbine (510); a plurality of nozzles (380) coupled between the lower nozzle plate (350) and the upper nozzle plate (370) to control the amount of fluid flowing into the turbine (510); a through pipe (356) coupled to the center of an upper surface of the lower nozzle plate (350) and passing through the lower nozzle plate (350) and the upper nozzle plate (370); and a control pipe (322) rotating inside the through pipe (356) for opening and closing the nozzles (380).