DESCRIPTION

METHOD OF OBTAINING POWER FROM POTENTIAL DIFFERENCE Related Art:

The method of gaining movement from the hot gas disposed from exhaust pipe of a jet plane is at least in similarity with our design.

The route that the plane traces is straight; however, it is annular in the turbine (3) of our system.

While the reaction is provided to the plane from the air remaining at its back, in our implementation, the reaction is provided to the turbine from the high density liquid resistance remaining at its back.

Also, dilation, which occurs by means of the friction loss in the waste liquid transforming into heat, increases this resistance.

The system's being adiabatic, a great amount of waste's including potential energy, effect and reaction of mechanic energy accumulating at the exhaust outlet point, the continuance of cycle movement enable the use of potential energy eternally without incurring any loss.

The rotation movement in the turbine is presented for use over the shaft (M) in its centre. In this respect, it is an engine with regard to its composition of design.

Attachments

Three illustrations. 1. The view of two reservoirs and their connections.

2. G-ό section.

3. Cooler schematic flow diagram and its mechanic cycle.

Reference Marks: 1- Small reservoir including cooling and the system liquid cycle starting point.

2- Big reservoir and its attachments.

3- Turbine.

4- Turbine centre shaft extension.

5- Gear part connected to no. (3) from the bottom. 6- Pump engine.

7- Turbine cycle engine.

8- Volume expansion protector. A- Pump suction pipe.

B- Pump. C- Pump force pipe.

D- Turbine vanes.

E- Turbine liquid venting holes.

F- Cross centring the turbine (4).

G- The part under turbine. I- Engine gear no. (7).

J- Turbine gear.

K- Reservoir brine part no. (1).

L- Intermediate pipe connecting (G) part liquid to the first reservoir.

M- Protruding end of the shaft no. (4). N- Site of filling water into the system, air venting and balancing the system pressure.

P- Roller bearing between turbine and (C) pipe.

R- Roller bearing between turbine and shaft no. (4).

S- Pipe where shaft no. (4) is embedded.

T- Protecting aperture of reservoir liquid no. (2). U- Liquid inlet point of reservoir no. one.

V- Upper part of reservoir no. one.

Y- Valve which evacuates apparatus no. (8).

W- Pressured oil box preventing (G) part liquid from leaking out.

Z- Liquid lower part of reservoir no. one. Description:

Two reservoirs (enclosed container) connected to each other with intermediate pipes. The one with no.2 is in the shape of cylinder. The liquid in the reservoirs is (Preferably) a composite (H ₂ O - HCI) metallic salt which improves the reaction. We inject (Assumption) 10 Bar air into the system from (N) part. (Of course this injected air is variable).

A turbine (3), which is self-enclosed and rotating around its own axis, is placed in and partially on the upper part of the reservoir no. (2). Pipe (C) is the extension of pump (B). It presses the liquid it has taken from part (Z) by means of line (A) and the turbine forms a composite with the centrifugal force. The liquid in turbine is vented through the apertures (E). Their number is (According to this drawing) eight. A contraction is present between the inlet sections those are at the top of venting holes and the outlet holes. By this means, the kinetic energy is increased. The (E)s are placed at the most distant peripheral part. The outlet direction of the liquid is at 180 degrees opposite direction of the rotation direction. Vanes (D) are present at the part corresponding to the top of the inlet surfaces. Their positions are 45 degrees angled according to the bottom surface. Angle corners are in the rotation direction. By this means, the vent liquid is forced to venting.

The shaft (4) extending downwards from the bottom centre of the turbine is in the pipe (S). This pipe is welded to the cross (F) from top, and to the base inner surface from bottom. Part (G) is present around it. This part is opened to the pipe (T). The section of this pipe is as the total of outlet sections of the venting holes (E).

The gear box no. (5) is present at outer and under reservoir. There is gear (J) in this box and the diameter of the gear is the same as the turbine diameter and it is connected to the shaft no.(4) from its centre, it transmits the movement of the gear (I) of the engine no. (7) to the turbine. Box (W) is present at the passage point of the shaft no. (4) at the part no. (5). This box is full of the thick oil wrapping the shaft. Equivalent air is injected into the system pressure through the check valve at the side part of the box and the air is stable. By this means, the liquid in the system is prevented from leaking out.

The friction occurring in the turbine vent pipes (E) transforms into heat. Dilation will occur in the natural liquid and that means expansion in the volume. The structure no. (8) is formed of a cylinder and a piston with a spring. The piston recesses when the volume expands. This recession continues to the valve (Y). If the volume expansion continues, the valve vents the excess by means of being opened. The liquid, which participates in the cycle, extends to the inlet (U) through the way (L). Meanwhile, if it is considered to utilize the heat, an amount of heat in the flow is used and the remaining reaches to the inlet (U) by the same way.

The reservoir no.(1) is two parts as being (V-Z). Copper pipe complex, which enables liquid passage to each other, is between these two parts. The liquid entering from (U) reaches to the part (Z) by means of passing through this complex. A brine (K) is placed between the pipes of the complex. The brine is cooled at a certain degree. The liquid which passes

through the copper pipes leaves the heat load remaining on itself here. CARNOT system may be used as well as using air and liquid in the cooling process.

As it is seen from the description, there is a liquid cycle system. The engines no.(6-7) enables this cycle. As the liquid that the turbine vents is at the opposite of rotation direction, it generates exhaust effect. The waste energy gains speed at the rotation direction due to the resistance that the periphery liquid volume shows. The main source of the effect in this mechanic energy is the potential which is in the system and which takes the whole system under its effect. The part of the potential and the kinetic energy resultant in the turbine part is operating by means of exhaust implementation and as a result of this operation it never incur losses.

In the turbine exhaust implementation, the potential part of the reservoir out of the turbine, dilation, the piston-spring no. 8 and the turbulence occurring at the cross (F) provide the effect.

The object in this design is to offer to use of the difference of the energy accumulating around the turbine and the centripetal force forming in the centre of the turbine on the shaft no. (4). Here, the system loses speed in the kinetic energy implementation; on the contrary, it gains from force as the potential takes under both effect and reaction and as it has to recess against the resistance. Because, this recessing energy transforms into rotation in the turbine. The liquid and air pressure placed in the system is unfailing and stable forever. The enthalpy of the system depends on its initial state and the state it will be in later. The load condition in the part (G) and its forward, the process of decreasing the gas require intervention in some circumstances by the CARNOT cycle. (Figure 3)

The evacuation amount of the enthalpy is at the amount of flow rate of the turbine. This condition determines this fact. The system enthalpy occurring in the part (G) will remain stable. This determines the force degree of the effect.

As there is a necessity of avoiding the heat load at the rotation route, this fact can be settled by means of utilizing various implementations of the current technology. The principles of a common cooling cycle belonging to this are shown schematically in (Figure 3). The compressor (A) sends the gas (CCI ₂ F ₂ , NH ₃ ) etc. to the serpentines (B) under high temperature and pressure. Heat is taken from the gas in (B) by water or air cooling and as a result the gas condensates to liquid phase under high pressure. This liquid passes through the smothery or expanding valve (C) and becomes into a mixture of liquid and gas at a lower temperature. Heat is given so as to transform the liquid remaining in the serpentines (D) into vapour and this vapour enters into the compressor (A) and the cycle starts again. In our system, the serpentines (D) are placed into the dense salty water or the like brine (K) around

the copper pipes of the reservoir no.(1). The system liquid passing through the copper pipes is drawn to the desired temperature and by this means equilibrium is provided by means of reaching to the level of the liquid in the cycle.

The cooling (Q1) in the flow diagram expresses the heat taken by means of the serpentines and the outer cooling (Q2) expresses the heat given (disposed) to the serpentines and (W) expresses the work done by the engine.