1. Technology Domain

The invention relates to a lift-creating rotor applicable in both air and liquid environments, such as vertical take-off and vertical landing aircrafts as well as to underwater crafts used in deep-water mass recovery, etc.

2. State of the Art Review

A conventional helicopter lift rotor is known to consist of radially arranged blades of airfoil profile fastened to the rotating shaft.

The solution currently known has the following drawbacks:

• the existing radial velocities of the blade profiles varying from the rotation axis to the periphery does not allow full utilization of the lift potential of blades;

• the rotation causes air turbulence and thinning which reduces the lift of the next rotation-wise blade and that necessitates practically the uεe of low-profile blades only;

• the known rotor design does not allow the use of an efficient system which could replace the helicopter tail propeller screw utilizing part of the engine power;

• during operation, a large vortex area iε formed around the aircraft which increases the drag in flight;

• a limited ceiling due to the thin air at high altitudes;

• non-feasibility of application in liquid environments.

3. Nature and Advantages of the Invention

The lift rotor consists of a centrifugal turbine fixed to a shaft in its centre of symmetry, of a conventional design; a hollow round casing with (a) centre hole(s) and vertical partitions arranged symmetrically and radially inside the centrifugal turbine casing forming side outlets on itε periphery. A wing representing an annular component iε fastened to the centrifugal turbine concentrically round itε periphery facing its side outlets. Screw-shaped ledges are fastened to the bottom and outside periphery of the wing.

The wing may be of a segmental design.

The rotor described here above can be used independently in helicopters with tail screws of the known conventional design. The lift rotor subject of the invention iε more efficiently used with stabilizer(s) substituting the function of the tail screw. The stabilizer(s) are flat components of an appropriate size and shape attached to the body of the helicopter and situated in the side opening area of the centrifugal turbine.

The invention also provides an opportunity for independent solution of the problem of aircraft propulsion by means of two rotors installed side by side perpendicularly to the longitudinal axis of the aircraft, turning in opposite directions in relation to each other. Here, the presence of an enclosure channelling the meeting flows from the side outlets of the two rotors iε also feaεible.

For higher ceiling, the invention envisageε an auxiliary independen -drive propeller screw mounted alongside the turbine shaft which, whenever required, can be positioned

vertically in a centre hole of the turbine, thus forcing more air through the εame opening.

A stronger lift, higher ceiling, localization of the vortices around the aircraft to facilitate the flight, use of a simplified and reliable substitute for the classical tail screw which saves engine power, are among the benefits of the invention; the rotor can be efficiently used in liquid environmen .

4. Description of the Figures

Fig.l showε plain view of the rotor subject to the invention illustrating the situation of the centrifugal turbine and that of the wing in relation to it;

Fig.2 showε a side half-view / half-section of the structure;

Fig.3 shows application of the invention in a helicopter along with the known tail screw;

Fig. shows the overall aircraft system - rotor with stabilizer - subject of the invention;

Fig.5 shows a plain view of an aircraft with two rotors and enclosure;

Fig.6 shows cross-section of the version with an extra propeller screw.

5. Implementation Examples

As shown in Figures 1 and 2, the lift rotor consists of a centrifugal turbine of known design fixed to a driving shaft through its basement, a hollow truncated-cone casing with an upper centre hole 2 , vertical partitions 3 arranged

symmetrically and radially inside the centrifugal turbine casing 1 forming side outlets on its periphery between the bottom and top of a truncated-cone shape. A wing 5 representing an annular component iε fastened to the centrifugal turbine concentrically round itε periphery facing its side outlets 4. Screw-shaped ledges 6 are fastened to the bottom and outside periphery of the wing. In an optional design, the wing 5 is made up of segments.

The invention can be used independently in helicopters with tail screws of the known conventional design (Fig.3). The invention, however, is more efficiently uεed with εtabilizer(s) 111 (εee Fig. 4) substituting the function of the tail screw. The stabilizer is a flat component of an appropriate size and shape attached to the body of the helicopter and situated in the side opening area 4 of the centrifugal turbine. The stabilizer angle is adjustable.

Fig. 5 shows an aircraft with two rotors for increased lift installed side by side perpendicularly to the longitudinal axis of the aircraft, turning opposite to each other. An enclosure {91 channelling the meeting air/fluid flows from the side outlets /4/ of the two rotors iε εituated εo as to enclose their wings and part of the centrifugal turbines.

For higher ceiling, the rotor design is supplemented with an auxiliary independent-drive propeller screw 181 mounted alongside the turbine εhaft /l/ (Fig. 6). Whenever required, the auxiliary screw 8 iε positioned vertically in the top centre hole of the centrifugal turbine 1, thuε forcing more air through the same opening.

The rotor operation is as below:

After setting it in a rotary motion, the radial velocities of the inner partitions 3 in the centrifugal turbine 1 will be different - increasing towards the periphery - therefore the

air velocity in the paεεages thus formed in the turbine will be analogical. As a result, the air/liquid medium will rush from the top centre hole 2 to the peripheral outlets 4 gradually increasing its velocity, and will entrain a new air or liquid mass until it is discharged through the peripheral outlets 4. The air/liquid mass streams down the airfoil 5 and creates a lift on the basis of the known aerodynamic principle. While streaming along the bottom surface of the wing 5, where the pressure is higher, the air/liquid mass impacts the surface of the screw-εhaped ledgeε 6 which have the highest radial velocity, and the air/liquid mass iε deflected in the direction determined by the screw profile creating a reactive propulsing force.

The new system with stabilizer εubstituting the functions of the tail screw (Fig. 1.) operates aε follows: the air/liquid mass flowing out of the peripheral outlets 4 at a high velocity encounters the εtabilizer surface 7 applying to it a force in the direction of rotation of the rotor . Thus the tendency of the aircraft body to rotate in the opposite direction is overcome.

When two rotors are used, they turn in opposite directions and the reactive propulsion created is stronger owing to the channeling effect of the enclosure.