WO2002038955A2

WO2002038955A2 - Power generating apparatus and lifting and propulsive force generating device

Info

Publication number: WO2002038955A2
Application number: PCT/KR2001/001892
Authority: WO
Inventors: Jae Hwan Kim
Original assignee: Individual
Current assignee: Individual
Priority date: 2000-11-07
Filing date: 2001-11-07
Publication date: 2002-05-16
Anticipated expiration: 2003-05-07
Also published as: AU2002215242A1; KR20020071928A; KR20020035703A

Description

POWER GENERATING APPARATUS AND LIFTING AND PROPULSIVE

FORCE GENERATING DEVICE

TECHNICAL FIELD The present invention relates to a structure coupling a turbine and a fluid compressor, an apparatus composed of a steel body using an operation principal of the structure, and an apparatus for obtaining a motive force by a lifting force generated in a structure for dispersing or absorbing a motion amount, in which the motive force, electric force, lifting force and propulsive force may be generated without using any energy source such as fuel to substitute the existing power generating system, thereby reducing the cost incurred by the providing of the energy source and the pollution due to the use of the energy source.

BACKGROUND ART The present invention belongs to the techniques in the fields of hydrodynamics and the motor engineering and derived to substitute the existing power sources or energy sources which in general burn fuels in the process of operation to obtain the motive force or the electricity, resulting in the atmospheric or environmental pollution due to the exhaust gas generated in the process of the burning. In the field, however, there has not been suggested any method for resolving the above disadvantages of the prior art .

DISCLOSURE OF THE INVENTION Therefore, the present invention is derived to resolve the above disadvantages and problems of the related art and has an object to reduce the pollution due to the exhaust materials caused by the use of fuels.

It is another object of the present invention to obtain motive force without using any fuels.

It is still another object of the present invention to obtain lifting and propulsive force in a belly of an airplane regardless of various geographical conditions and meteorological conditions.

According to one aspect of the present invention in order to solve the above problems,

BRIEF DESCRIPTION OF THE DRAWINGS

A more complete appreciation of the invention, and many of the attendant advantages thereof, will be readily apparent as the same becomes better understood by reference to the followings detailed description when considered in conjunction with the accompanying drawings, in which like reference symbols indicate the same or the similar components, wherein: Fig. 1 is a view for explaining a structure according to a preferred embodiment of the present invention;

Fig.2 is a view for explaining a structure of a first part (turbine wings) of Fig. 1 ; Fig. 3 is a cross-sectional view showings the first part according to another preferred embodiment of the present invention;

Fig. 4 is a view for explaining a structure of a second part (compression wings) of Fig. 1 ; Fig. 5 is a cross-sectional view showings the second part of Fig. 4 according to another embodiment of the present invention; Fig. 6 is a cross-sectional view showings the second part of Fig. 4 according to a further embodiment of the present invention;

Fig. 7 is a cross-sectional view showings the second part of Fig. 4 according to a still another embodiment of the present invention;

Fig. 8 is a cross-sectional view showings the second part of Fig. 4 according to a still further embodiment of the present invention; Fig. 9 is a view for explaining a structure according to a second preferred embodiment of the present invention;

Fig. 10 is a cross-sectional view showings a structure of a part 40 (guiding wings) of Fig. 9; Fig. 11 is a view for explaining a structure according to a third preferred embodiment of the present invention;

Fig. 12 is a view for explaining a structure according to a fourth preferred embodiment of the present invention;

Fig. 13 is a view for explaining a structure according to a fifth preferred embodiment of the present invention;

Fig. 14 is a view for explaining a structure according to a sixth preferred embodiment of the present invention;

Fig. 15 is a cross-sectional view showings a structure of the second part (compression wings) of Fig

14; Fig. 16 is a cross-sectional view showings a structure of the first part (turbine wings) of Fig. 14;

Fig. 17 is a view for explaining a structure according to a seventh preferred embodiment of the present invention;

Fig. 18 is a cross-sectional view showings a structure of parts lf-lh (turbine wings) of Fig. 17; Fig. 19 is a view for explaining a structure according to an eighth preferred embodiment of the present invention;

Fig. 20 is a cross-sectional view showings a structure of a wings for combined use as turbine wings lf-lh, guiding wings and the turbine wings 40a-40b of Fig. 19;

Fig. 21 is a view for explaining a structure according to a ninth preferred embodiment of the present invention; Fig. 22 is a cross-sectional view for showings a structure of a wings for combines use of turbine wings lf-lh, guiding wings, turbine wings 40a-40b and compression wings 22 of Fig. 21;

Fig. 23 is a view for explaining a structure according to a tenth preferred embodiment of the present invention;

Fig. 24 is a view for explaining a structure according to an eleventh preferred embodiment of the present invention; Fig. 25 is a cross-sectional view for showings a structure of parts If, 2d and 40a of Fig. 24;

Fig. 26 is a view for explaining a structure according to a twelfth preferred embodiment of the present invention; Fig. 27 is a cross-sectional view showings a part 65 of Fig. 26;

Fig. 28 is a cross-sectional view showings the part of Fig. 27 according to another embodiment of the present invention;

Fig. 29 is a view for explaining a structure according to a thirteenth preferred embodiment of the present invention;

Fig. 30 is a side sectional view of Fig. 29;

Fig. 31 is a partial perspective view showings a structure of parts 71 and 74a of Fig. 30;

Fig. 32 is a view of Fig. 30 according to another embodiment of the present invention;

Fig. 33 is a view for explaining a structure according to a fourteenth preferred embodiment of the present invention;

Fig. 34 is a view for explaining a structure according to a fifteenth preferred embodiment of the present invention;

Fig. 35 is a perspective view showings a structure of a part 140 of Fig. 31;

Fig. 36 is a partial cross-sectional view showings a part 148 of Fig. 31 according to another embodiment of the present invention;

Fig. 37 is a perspective view showings a structure of a part 150 of Fig. 31;

Fig. 38 is a schematic cross-sectional view for explaining a structure according to a sixteenth embodiment of the present invention; and

Fig. 39 is a side cross-sectional view of Fig. 38.

BEST MODE FOR CARRYING OUT THE INVENTION

The present invention will be explained in more detail with reference to preferred embodiments in junctions with the attached drawings .

Fig. 1 is a view for explaining a structure according to a preferred embodiment of the present invention. In Fig. 1, a sealed cylindrical case 10 is mounted with a centripetal turbine wings 1 and a centrifugal compression wings 2 is mounted in the vicinity of the turbine wings, wherein a compressor refers a wings type blower and a compressor inclusively. A rotation shaft 18 of the turbine wings and a rotation shaft 14 of the compression wings are connected to each other by power transmission unit 11-13 in such a manner that the compression wings 2 and the turbine wings 1 rotate in the same direction and a rotation velocity of the compression wings 2 is higher than that of the turbine wings 1. In the cylindrical case, a fluid such as a liquid like water or a gas passes through the turbine wings 1, which is fixed to the rotation cylindrical case 10 to be introduced in the centripetal direction. The fluid rotates in the spiral direction to be introduced to the compression wings 2 to forward in the centrifugal direction. Then the fluid is re-introduced into the turbine wings 1, thereby circulating. The turbine rotation shaft 18 is mounted with a driving motor 3. In the apparatus as described above, a motive force obtained from the fluid in the turbine wings 1 is larger than a motive force applied to the fluid by the compression wings 2, so that the apparatus may operate by the motive force obtained in itself by the reasons as mentioned below. The structure of the turbine wings 1 is different from that of an existing turbine wings, as shown in Fig. 2, Fig. 3, Fig. 7 and Fig. 8. A circular plate 20 has a circumference 21 which is formed with a very small angular difference, and a plurality of wings la- Id are mounted in the shape of spire in such a manner that sectional areas of flow channels 22 between the wings become narrower gradually in the centripetal direction toward a center of the rotation shaft 18, so that outer tangent lines of concentric circles almost agree with mounting angles of the spiral wings la-Id. According to the characteristics of this structure, the fluid is introduced into the centripetal part after circulating the flow channels in the turbine wings and a direction of the fluid in the vicinity of outlets 6 of the turbine wings almost agrees with a rotation direction of end parts 23 of the turbine wings .

Therefore, since there is a small angle difference between the direction of the fluid at the outlets and the rotation direction of the wings end parts 23, an absolute velocity of the fluid has little difference in comparison with the velocity inlets 8a of the flow channels of the turbine wings. If the angular difference between the fluid direction and the wing rotation direction becomes larger, the absolute velocity synthesized by respective velocity components becomes reduced. To the contrary, if the angular difference becomes smaller, the absolute velocity reduces little.

Further, as a turning radius difference between front ends 24a and rear ends 24b of the wings becomes larger, a larger torque may be obtained.

As described above, according to the apparatus of the present invention, the torque is generated in the turbine wings 1 with a small reduction of motion energy of the fluid, so that the fluid, which passed through the flow channels 25 between the turbine wings, has large motion energy. The fluid discharged via the outlets 6 passes through the compression wings, complementing the reduced motion energy. If the fluid discharged via the outlets 7 of the compression wings continues the circulation by being re-introduced to the turbine wings 1, the motive force, which is obtained by the turbine wings 1, becomes larger than that applied to the compression wings 2.

Therefore, the rotation force of the turbine wings 1 is partially utilized for rotating the compression wings 2 and the remaining is utilized for obtaining electricity or operating other machines by a power transmission unit 26. It is also possible to mount a generator, which is not shown, to the rotation shaft 18 of the turbine wings to use the rotation shaft 18 as a common rotation shaft for both the turbine wings and the generator, thereby operating the generator in a normal operation mode.

The apparatus has a structure for rotating the compression wings 2 with a part of the motive force obtained by the turbine wings 1, so that the rotation velocity changes according to a load of the used motive force. Therefore, the rotation velocity has to be controlled for obtaining the electricity of a uniform frequency .

In order to keep the uniform velocity, a semiconductor element is mounted to an output conduit of the generator for controlling a current. As an output voltage is increased, the current should be increased. The rotation shaft 18 of the turbine wings is mounted with an eddy current brake system for operating the eddy current brake system by increasing the current flowing in the eddy current brake system, thereby controlling the velocity. Also, other conventional device maybe employed for controlling the velocity .

In the above case, the sectional areas of the flow channels 25 between the turbine wings la- Id are larger at the inlets 26a rather than at the outlets 26b. Further, it is preferable to decrease the sectional areas gradually in proportion to a reduction ratio of the turning radius. If the sectionals areas of the flow channels are uniform, the absolute velocity of the fluid becomes decreased and a pressure becomes increased, decreasing the efficiency.

As for the structure of the turbine wings 1, the long and thin wings la- Id may be formed as shown in Fig. 2. In order to form the wings short as shown in Fig. 3, center portions 29 of the wings have to be formed thicker. Further, as shown in Fig. 7, even shorter wings 30 may be mounted for reducing the length of the flow channels. As the length of the wings becomes longer, the operation efficiency becomes higher, wherein friction loss becomes larger due to the longer flow channels.

The structure of the wings may be selected in consideration of the advantages and disadvantages of the above three embodiments, wherein the angular difference between the circular plate and the outer circumference in the inlet parts of the flow channels has to be minimum, a radius of curvature has to be gradually decreased, and the direction of the fluid at every possible position and the direction of rotation of the wings has to be kept not large.

Referring to Fig. 4, the compression wings 2 are formed in a curved wing structure that sectional areas of flow channels 33 between the wings are increased gradually and an angular difference between a mounting angle of wings 35a and an outer circumference is kept very small. Also, referring to Fig. 5, the compression wings are formed in the straight structure or with slightly curved rear surfaces 36, wherein the sectional areas of flow channels 33 between the wings are increased gradually and the angular difference between the mounting angle of wings and an outer circumference is kept very small.

As the compression wings structured as above rotate, a velocity difference is generated in the relative motion of the fluid and the wings while the wings passing through the fluid since the sectional areas of the flow channels increase gradually, thereby the relative velocity of the fluid in the flow channels between the wings becomes decreased gradually.

That is, the absolute velocity of the fluid increases gradually in the rotation direction of the wings and the pressure also increases gradually.

According to the above operation principle, a compressor of a high efficiency may be realized, wherein especially, the efficiency becomes higher as the velocity difference between front ends 38a and rear ends 38b of the wings 2 becomes smaller and the angular difference between the rotation direction and the angle of the wings becomes smaller. As described hereinabove, the compression wings la-Id are formed in the structure for passing through the fluid and the wings rotate in the direction that the fluid rotates, and the flow ratio is not increased if the rotation velocity of the wings is not higher than the velocity of the fluid, so that an amount of the fluid which is introduced into the flow channels 33 between the wings becomes different according to the velocity difference between the wings and the fluid, that is, the relative velocity. Therefore, the efficiency is higher in a structure that an expansion ratio of the flow channels between the wings is smaller than the other case . The compression wings 2 may be formed in the structure as shown in Fig. 6. In Fig. 6, short and straight wings are mounted radially and a turning radius of front ends and rear ends of the wings is small, so that the velocity of the front end parts 38a of the wings becomes almost equal to the velocity of the fluid for increasing the efficiency, wherein the increase of the fluid velocity is proportional to the velocity of the rear end parts 38b of the wings.

Referring to Fig. 8, the front ends 24a of the wings are mounted with a smaller angle with the circumference and the rear ends 24b of the wings are mounted with a larger angle in the rotation direction, wherein the sectional areas of the flow channels 8a are narrower at the front ends and wider at the rear ends .

Therefore, the relative velocity of the fluid is largely reduced in the flow channels between the wings so that the velocity at the outlets 8b is very slow, wherein the velocity component the fluid is discharged at a velocity, which is almost equal to that of the rear end parts 24b. According to the above structure, even though the fluid velocity is decreased in the flow channels between the turbine wings 1, the efficiency is high since the velocity component of the fluid is converted to a pressure. Therefore, in order to increase the efficiency, the velocity difference between the front ends 24a and the rear ends 24b of the wings has to be kept small, so that it is preferable to increase a number of the wings.

The pressure of the fluid which is increased in the flow channels 25 between the wings, is converted to the velocity component at a position where the sectional areas of the flow channels are narrow, or complements the friction loss of the fluid which is generated in the process of operation, so that the fluid velocity is not decreased in the flow channels. Further, due to the structure of the compression wings 2 increasing the efficiency, the motive force larger than the motive force used by the compression wings 2 may be obtained. Since heat is generated in the fluid in the apparatus, in order to prevent the rising of the temperature of the fluid, flow channels 9a and 9b are connected to an outside of the cylindrical case 10 for circulating the fluid. Further, a cooling fan, which is not shown, may be mounted to directly cool the cylindrical case 10, or the cylindrical case 10 may be cooled by natural convection. In the above apparatus, an internal pressure becomes changed according to the temperature of the fluid in the apparatus . In order to keep the pressure of the fluid uniform or control the pressure to a proper value as necessary, it is preferable to mount a pressure control unit 4 for the internal fluid, which may be selected among the conventional ones and mounted in a proper structure. The pressure control unit 4 is communicated with the fluid in the cylindrical case 10 via a hole 19 formed in the rotation shaft 18.

Fig. 9 is a view for explaining a structure according to a second preferred embodiment of the present invention, wherein the structure is equal to that of the first embodiment of the present invention except that the compression wings 2 are formed with a small turning radius and mounted with guide wings 40 outside. The fluid at the outlets of the compression wings 2 flows outwardly while rotating in the spiral direction, wherein the velocity of the fluid becomes decreased and the pressure of the fluid becomes increased due to the centrifugal force. Therefore, the guide wings formed with flow channels in the spiral direction as shown in Fig. 10 are mounted in order to prevent the decrease of the flow ratio, and the sectional areas of the flow channels 41 between the wings are kept uniformly.

Accordingly, the fluid which is discharged via the outlets of the compression wings 2 rotates spirally via the flow channels between the guide wings 40, and transferred toward the circumference where the turning radius of the cylindrical case 10 is larger, so as to be introduced into the inlets 8a of the turbine wings. Fig. 11 is a view for explaining a structure according to a third preferred embodiment of the present invention, wherein the structure is equal to that of the first embodiment of the present invention but the compression wings 2 rotate in a different manner.

In the first preferred embodiment of the present invention, the motive force of the turbine wings 1 and the motive force of the driving motor 3 are transmitted to the compression wings 2 by the power transmission unit 11-13. However, according to the third embodiment of the present invention, a rotation shaft 3a of the driving motor 3 is mounted to the rotation shaft 18 of the turbine wings to rotate and the compression wings 2 are mounted to the rotation shaft of the driving motor.

An input current of the driving motor 3 is supplied from the outside via a slip ring 48. Therefore, it is not necessary to connect the rotation shaft 18 of the turbine wings and the rotation shaft of the compression wings 2 and the velocity of the compression wings 2 may be controlled randomly, thereby simplifying the control of the apparatus. Fig. 12 is a view for explaining a structure according to a fourth preferred embodiment of the present invention, wherein turbine wings lf-lh and guide wings 40a-40b of the structure according to the second embodiment of the present invention are stacked in multiple stages for preventing the disadvantage of the single stage structure, that is, reducing the friction loss and increasing the velocity of the fluid, thereby obtaining a large motive force.

Since the velocity of the fluid may be reduced while passing through the turbine wings lf-lh of the respective stages, it is preferable to form the flow channels in such a manner that the sectional areas of the flow channels increase gradually in the respective stages of the turbine wings lf-lh if gas is used as the working fluid. However, a difference of the pressure is not large according to the structure and operation manner of the compression wings 2. Therefore, the sectional areas of the flow channels of the respective turbine wings lf-lh and the guide wings 40a-40b may be formed almost uniformly. If a liquid is used as the working fluid, it is preferable to form the flow channels with uniform sectional areas since a volume difference of the fluid is very small due to the difference of pressure of the fluid. However, even in the case of liquid, it is possible to form the sectional areas between the respective turbine wings lf-lh and the guide wings 40a, 40b to be expanded gradually in a structure that the fluid pressure is not largely increased in the compression wings 2.

Fig. 13 is a view for explaining a structure according to a fifth preferred embodiment of the present invention, wherein the structure and the operation manner are almost equal to those of the fourth embodiment of the present invention but no guide wings are provided.

Therefore, the fluid pressure may be increased and the flow ratio may be decreased due to the centrifugal force during the fluid flows from the outlets 6a-6c of the turbine wings in the centrifugal direction. Further, a loss may be generated by the conversion from velocity energy to pressure energy or vice versa, but the loss is not large.

Fig. 14 is a view for explaining a structure according to a sixth preferred embodiment of the present invention, wherein the structure is equal to that of the first embodiment of the present invention but the turbine wings 1 and the compression wings 2 are formed in different structures . The compression wings 2 have a wide width as shown in Fig.15 to reduce a number of required wings 2a-2c, wherein a difference between a rotation direction of the wings and a mounting angle of the wings is very small by reducing the mounting angle of the wings so that the load is very small .

Therefore, the increase of the fluid velocity is small in view of the rotation velocity of the wings and the fluid velocity is increases mainly in the perpendicular direction with respect to the rotation direction, so that the turbine wings 1 obtains rotation torque by the velocity component of the fluid which is applied in the perpendicular direction (normal line direction) with respect to the turbine wing directions as shown in Fig. 16.

The structure of the turbine wings 1 is similar to that of water mill of low head and the mounting angle of the wings is very large, so that the rotation velocity of the turbine wings 1 is slower than that of the compression wings 2 but has a larger rotation torque.

However, the rotation velocity of the cylindrical case 10 is high so that absolute velocity ratios of the turbine wings 1 and the compression wings 2 are not high.

Therefore, the compression wings 2 are rotated by a part of the rotation force of the turbine wings 1 and the remaining force may be used.

Fig. 17 is a view for explaining a structure according to a seventh preferred embodiment of the present invention, wherein turbine wings lf-lh are mounted with a very small angular difference with respect to the rotation direction and formed of thin and long wings as shown in Fig. 18 mounted in multiple stages in the centrifugal direction concentrically. Front end parts 50 of the wings are sharpened as shown in Fig. 18 or rounded, and the flow channels 50a-51 between the wings from the front end parts 50 to rear end parts are formed with a uniform sectional area, so that the fluid is discharged with an increased velocity while passing from the front end parts 50 along the flow channels 50a between the wings. The discharged fluid passes along the flow channels between the wings in the turbine wing lg of a next stage without any velocity reduction, thereby increasing the velocity much more. A pressure of the fluid which is applied to belly part surfaces 53a of the turbine wings is larger than that of the rear surfaces 53b, so that the turbine wings rotate by the pressure difference not by the velocity energy of the fluid.

Therefore, the loss of the fluid energy becomes very small, obtaining high efficiency.

However, the fluid works at the belly part surfaces 53a of the wings, and at this time the pressure energy is used, so that the temperature of the fluid becomes lowered in this operation procedure.

Such the working fluid may be gas or liquid. In case of liquid, since the gas becomes expanded in the process of operation, the flow channels between the respective stages lf-lh are formed in the structure that the sectional areas become increased gradually. In case of liquid, since the velocity of the fluid itself increases, the sectional areas between the respective stages are reduced gradually wherein an interval between both side plates 54a and 54b of the turbine are gradually reduced for reducing the sectional areas of the flow channels gradually. The fluid passing though the turbine wing lh of the final stage passes through the turbine wing li of a spiral structure equal to that of the first embodiment to be introduced into the centripetal part. The spiral wing li rotates in a reverse direction, so that the forces from the rotation force 18a of the reaction type turbine wings and the power transmission unit 55 transmitted to each other. The compression wings 2 rotate at a very high speed, so that the efficiency becomes higher. Therefore, it is also possible to mount the compression wings in the multiple stages .

After the fluid velocity is increased in the compression wings, the fluid velocity is highly reduced by the guiding wings 40a but the pressure is increased to be recycled. In order to raise the temperature of the cooled fluid, the fluid is heated by a heat medium circulating through a heating tube 56, wherein a fluid in the heating tube 56 is cooled so that it is also possible to use the present apparatus as a cooling device. That is, the temperature of the working fluid may be lowered regardless of the external temperature, so that it may be possible to obtain power and simultaneously using the apparatus as a cooling device.

Fig. 19 is a view for explaining a structure according to a eighth preferred embodiment of the present invention, wherein the structure and the operation principle are similar to those of the seventh embodiment of the present invention. In Fig. 19, guiding wings in addition serving as turbine wings 40a-40b are mounted between the turbine wings lf-lh of the respective stages for increasing the velocity of the fluid by the turbine wings lf-lh in the respective stages to discharge the fluid, so that the velocity energy of the fluid is converted to the pressure energy and the guiding/turbine wings 40a-40b obtains the rotation force from the pressure. Further, the front end parts 50 of the turbine wings are sharpened as shown in Fig. 18, or rounded as shown in Fig. 20 in order to obtain a larger force. The fluid passing through the turbine wings lf-lh in the respective stages becomes increased in the velocity, but the velocity of the fluid becomes reduced while the pressure thereof becomes increased by the structure of the flow channels 60 formed between the guiding/turbine wings 40a-40b that the sectional areas are expanded

The structure of the guiding/turbine wings 40a-40b is similar to that of the compression wings as shown in Fig. 4 and Fig. 5 showing the first embodiment of the present invention, wherein the guiding/turbine wings 40a-40b obtains the force by the operation carried out a reverse procedure of the compression procedure. The rotation direction is opposite to that of the turbine wings lf-lh and the guiding/turbine wings are connected to the power transmission unit 55. Even though it is also possible to fix the guiding/turbine wings 40a, 40b to serve only as the guiding wings, the efficiency is higher when the wings are utilized as both the guiding and turbine wings.

Fig. 21 is a view for explaining a structure according to a ninth preferred embodiment of the present invention, wherein the operation principle is similar to that of the eighth embodiment but the guiding/turbine wings are structured in the axial flow type. The guiding/turbine wings 40a-40b may be fixed to serve as the guiding wings only but rotate to serve as the turbine wings too, thereby increasing the efficiency. The guiding/turbine wings 40a, 40b is structured in the same shape with the short turbine wings as shown in Fig. 8 which shows the first preferred embodiment of the present invention.

The compression wings 2 operate in the same manner with that of the compression wings as shown in Fig. 4 and Fig. 5 which show the first embodiment, wherein the compression wings 2 are in the axial flow type with wings which are formed straightly long and thick at the front end parts so that the friction between the front end parts 62 and the fluid becomes minimized when the wings are rotating . The difference between the rotation direction of the wings and the mounting angle of the wings is very small and the thickness of the front end parts 62 of the wings are thick as shown in Fig. 22 so that the sectional areas between the flow channels 63 between the wings become expanded gradually. The belly part surfaces and the rear surfaces of the wings may be curved but preferably straight for increasing the efficiency.

Further, it is prevented the front end parts 62 of the wings from being thick excessively for minimizing the friction loss of the fluid in the process of the rotation of the wings .

Fig. 23 is a view for explaining a structure according to a tenth preferred embodiment of the present invention, wherein the turbine wings lf-lh formed in the centrifugal type and the compression wings 2d-2f are mounted in the multiple stage structure, wherein the structure of the wings are equal to that of the compression wings 2 of Fig. 15 and the turbine wings of Fig. 16 according to the sixth embodiment. In the compression wings 2, the fluid velocity component is increased in the rotation direction of the wings and the perpendicular direction of the wings and the increase of the fluid is small in comparison with the velocity of the wings 2.

Therefore, the rotation load is very small and the rotation velocity is very high. To the contrary, the turbine wings 1 have a very high torque and rotate very slowly in comparison with the compression wings . However, the rotation velocity of the cylindrical case 10 is high so that the absolute velocity ratio between the turbine wings lf-lh and the compression wings 2d-2f is not large. Therefore, the force obtained by the turbine wings is larger than that used by the compression wings, so that the force remained after rotating the compression wings may be utilized.

Fig. 24 is a view for explaining a structure according to a eleventh preferred embodiment of the present invention, wherein the structure of the turbine wings lf-lh is equal to that of the tenth embodiment but the structure of the compression wings 2d-2f is different. Further, guiding wings 40a, 40b are mounted to correct the direction of the fluid. The structure of the compression wings is equal to that of the ninth embodiment as shown in Fig. 22, so that the velocity component of the fluid is increased in the rotation direction by the compression wings 2d-2f and the velocity component of the fluid, which is increased by the guiding wings 40a, 40b, is corrected to lean in the perpendicular direction of the rotation direction of the turbine wings while passing through the guiding wings 40a, 40b.

That is, the compression wings 2d-2f increase the velocity of the fluid in the rotation direction of the compression wings and the velocity component of the fluid is converted to the velocity component in the axial direction by the guiding wings 40a, 40b, so that the velocity component in the axial direction is highly increased to work in the turbine wings lf-lh. Therefore, the large force may be obtained and the force obtained by the turbine wings is larger than that used by the compression wings, so that the force remained after rotating the compression wings may be utilized.

Fig. 26 is a view for explaining a structure according to a twelfth preferred embodiment of the present invention, wherein the structure of the turbine wings 1 is equal to that of the sixth embodiment and the structure of the compression wings 2 is equal to that of the first embodiment.

Further, guiding wings 65 in addition serving as turbine wings are mounted to outer parts of the compression wings. The guiding/turbine wings 64 convert the direction of the fluid of which the velocity component is increased in the rotation direction of the wings in the compression wings 2, to increase the velocity component of the fluid in the perpendicular direction of the rotation direction of the turbine wings 1. The guiding/turbine wings 64 rotate by the pressure applied to the surfaces of the wings in the process of the direction conversion of the fluid.

It is possible to control the rotation velocity of the wings 65 high or low. In order to control the rotation velocity of the wings 65 high, the fluid direction is converted with a large angle in the flow channels between the wings by increasing the angle of the wings, while the absolute velocity of the fluid in the rotation direction of the wings maintained equal to that of the fluid before the fluid is introduced into the compression wings 2 by converting the flow direction with a small angle in the other case.

Also, it is possible to mount the guiding/turbine wings 65 in the axial flow direction as shown in Fig. 28. The sectional area of the flow channels 67 between the wings has to be maintained uniformly. Since the width of the flow channels is expanded by the direction conversion of the fluid, the length of the wings has to be shorten gradually and the interval between the both side plates 68a and 68b has to be narrower gradually, so that the sectional areas of the flow channels become expanded.

As described above, in this embodiment, it is possible to obtain increased efficiency by the two turbine wings .

Fig. 29 and Fig. 30 show a structure according to a thirteenth preferred embodiment of the present invention, in which the force may be obtained by the spiral motion of a steel body. The force obtained in the process that the fluid passes through the turbine wings la-Id of Fig. 2, Fig. 3 and Fig. 7 showing the first embodiment is larger than the motion energy that the fluid has lost .

A rotation cylindrical case 70 is symmetrically mounted with wing pieces 72a, 72b which are structured with inner surfaces 75a-75b having a radius of curvature which decreases gradually, and rollers 71a-71d rotatably inside . Supporting shafts 73a-73d of the rollers are slightly inclined with respect to the normal line direction and mounted perpendicularly to the inner surfaces of the wing pieces where the radius of curvature is smaller. The supporting shafts are mounted with springs 74a-74d at the other ends where the rollers are not mounted. If an inner cylindrical case 77 rotates, the rollers 71a-71d of larger mass rotate in association, pressing the inner surfaces 75a-75b of the wing pieces.

The rollers compress the springs 74a-74d by the centrifugal force, and rotate in contact with the inner surfaces 75a-75b of the wing pieces where the radius of curvature is smaller than the inner surface 70a of the circumference of the rotation cylindrical case 70. Therefore, the rollers push the inner surfaces of the wing pieces with a large centrifugal force, and apply a torque to the rotation cylindrical case 70 in the rotation direction of the rollers, thereby rotating the larger cylindrical case 70.

The rollers 71a-71d rotate by an electric motor 88. While the rollers rotate, the rollers push the inner surfaces 75a, 75b of the wing pieces. Further, the rollers reciprocate movement in the centripetal direction of the cylindrical case 70 and in the centrifugal direction.

The rotation torque of the rollers becomes increased while the rollers move in the centripetal direction, and decreased in the other case. Therefore, almost no force is used in the process of rotating the rollers except the friction loss . However, the cylindrical case 70 mounted with the wing pieces 72a, 72b obtains a high torque due to the centrifugal force of the rollers, and the force obtained by this large torque may used for generating the electricity from a generator 80 mounted to rotation shaft 78 of the cylindrical case. As the obtained electricity is supplied to the electric motor 88 partially, the rollers 71a-71d rotate continuously, generating the electricity continuously. Remaining of the generated electricity or the force obtained by the power transmission unit 16 mounted to the rotation shaft 78 may be utilized further.

Fig. 32 shows another embodiment of Fig. 31. In Fig. 32, instead of mounting the electric motor to the rotation shaft of the cylindrical case 70, the rotation shaft 78 of the rollers are connected to the rotation shaft of the cylindrical case 70 by the power transmission unit 11-13 for transmitting the force to each other.

Fig. 33 is a view for explaining a structure according to a fourteenth preferred embodiment of the present invention. In Fig. 33, electric motors 101a, 101b or engines are rotated at a high speed, for moving a piston 108 connected to the rotation shaft of the electric motors or the engines by a crank shaft at a high speed. A cylinder 127 at a lower part of the piston 108 is filled with a liquid inside and formed with holes 122a-122d at a side surface for inflowing or outflowing the liquid filled in the cylinder with respect to outer spaces 135a-135d. The cylinder is mounted with spherical tubes 130a-130d, which are filled with gas, inside by a predetermined interval (the tubes may be filled with elastic elements of different structure from gas) . The outer spaces 135a-135d filled with the liquid are mounted with ring-shaped tubes 131a-131d, which are filled with gas. In the above apparatus, the downward motion amount of the steel element, which carries out vibration motion, is dispersed and absorbed for generating upward lifting force. If a very faster and larger motion amount is generated by the electric motors or the engines 101a, 101b, a larger upward lifting force may be obtained. Therefore, this apparatus may be used for generating the lifting force in the air planes and ships or generating power in the air planes or vehicles. If the apparatus is mounted in an air plane, it is possible to take off or land the air plane vertically and carry out the flying without using any fuel, thereby improving the safety. Further, a plurality of such apparatus is mounted in a rotation cylindrical case symmetrically for rotating the cylindrical case by the lifting force as shown in Fig. 34, it is possible to obtain a large force. Therefore, the apparatus may be utilized as the power generating system, of which the operation principle is as described hereinafter.

If the piston 108 moves downwardly, the liquid 133a at the lower part has an increased inner pressure due to the pressure of a surface 109 of the piston, discharging the liquid in the cylinder 127 via the holes of the cylinder. Further, the tubes 130a at the lower part of the piston retracts due to the downward pressure applied to the liquid and the liquid flows downwardly.

Due to the pressure in the liquid, the velocity of the liquid, which moves downwardly and toward the outer spaces 135a, is different according to the mass of the liquid, the velocity of the downward piston surface 109 and a time period that the pressure is continuously applied by the piston surface 109. The piston 108 moves vertically by a predetermined period since the motion energy generated by the rotation of the electric motors 101a, 101b is converted to the vertical motion of the crank shaft 103 and the motion energy of the vertical motion of the crank shaft 103 is transmitted to the piston downwardly. Therefore, the liquid below the piston carries out the wave motion by flowing downwardly and upwardly.

A downward motion amount is gradually reduced by the liquid which is discharged via the holes at the side surface of the cylinder while being transmitted to the several stages 133a-133d at the lower part, so that a pressure which is finally applied to a bottom surface 137 is smaller than the motion energy which is applied to the liquid 133a by the piston surface 109. Therefore, a time period taken for the liquid to be restored to an initial state by the upward flowing is longer that a time period taken for the liquid to flow downwardly. That is, after the motion energy of the liquid is reduced, an upward repulsive force is generated by the reduced motion energy so that the upward velocity is low, thereby increasing the time period for the upward flowing of the liquid. In the waves formed in the liquid of the respective stages 133a-133d, it is preferably to form a first wave in the second stage. If the wave smaller than the first wave is generated in the previous stage, the reduction of the wave energy becomes reduced, thereby decreasing the energy efficiency.

Fig. 34 is a view for explaining a structure according to a fifteenth preferred embodiment of the present invention, which utilizes the operation principle of the steel element of the sixth embodiment. In the process of transmitting motion amounts between two steel elements 140 and 150, which are mounted for moving perpendicularly to each other, the upward lifting, force is generated. Contact portions of the steel elements are formed curvedly with an angle displacement of 90° . The motion energies of the steel elements are transmitted to the upward steel elements while the motion direction is continuously changed by the downward direction by the curved surfaces of the contact portions.

The horizontal steel element 140 of which the motion energy is reduced moves upwardly by the repulsive force after the downward movement. In this case, a piston 153 mounted at a lower part of the horizontal steel element 140 moves vertically in a cylinder 152 and the liquid inflows or outflows via holes formed in the piston 153, thereby reducing the motion energy. Further, when the steel element 140 moves upwardly, a piston 143 mounted at an upper part of the steel element moves vertically in a sealed cylindrical case 148, so that the liquid inflows or outflows via holes formed in the piston, thereby reducing the motion energy. In the above case, the motion energy of the vertically moving steel element 140 is reduced by the below reason. When the piston 143 moves upwardly in the cylindrical case 148 which is filled with liquid and sealed, a large hole 144 formed in the piston is blocked off by a valve 147 and a pressure of the liquid (or gas) in the cylindrical case in increased, so that the fluid at an upper part 146b is discharged to a lower part 146a via small holes 145 by the pressure, and in this procedure, a motion energy of the liquid passing through the holes at a high speed is obtained by the pressure applied to the liquid by the upwardly moving piston 143.

In the procedure, the motion energy of the steel element 140 is reduced and a downward motion energy after the upward movement is obtained by a spring 149. Even though the motion energy is reduced by the liquid flowing out via the upper hole 146b, the pressure applied to the liquid at the lower part 146a is weak so that the liquid is almost stopped when the steel element 140 reaches an initial position.

The horizontally moving steel element 150 moves upwardly after the reduction of the motion energy by a liquid in a piston 153, which is mounted at a lower part, by a motion energy remained after being transmitted to the vertically moving steel element 140 in the same manner with the vertically moving steel element.

In the above case, motion energy reduction elements 152, 148 that are respectively mounted to the two steel elements are formed in a structure for converting the motion energy of the steel element to the motion energy of the liquid, generating the energy loss.

Fig. 36 shows an apparatus for converting the motion energy to the electricity without any loss of the motion energy. In Fig. 36, magnets 174 are mounted to the vertically moving steel element 140 and a core 175 wound with coils 177 is mounted in the vicinity of the steel element for converting the motion energy of the steel element to the electricity, wherein the same structure may be adopted to the steel element which moves horizontally.

The horizontally moving steel element 150 carries out the vertical motion simultaneously. Accordingly, an axial rod 159 is rolled vertically. In Fig. 37, the axial rod is connected to a piston 160 and a roller 158 is mounted to a lower supporting die at a lower part of the steel element , thereby moving the steel element smoothly.

According to the structure described above, the motion energy obtained by the horizontally moving steel element 150 from an electric motor 170 is transmitted to the vertically moving steel element 140 a lot, and the horizontally moving steel element 150 moves downwardly by the remaining motion energy, thereby generating the upward lifting force in the apparatus.

Fig. 38 is a view for explaining a structure according to a sixteenth preferred embodiment of the present invention. Referring to Fig. 38, rotation cylindrical case 180 is mounted with a plurality of lifting force generating elements 181a, 181b in the vicinity of an inner circumference. If the lifting force of the lifting force generating elements 181a, 181b are generated in the same direction, the cylindrical case becomes rotating by the lifting force generated by the lifting force generating elements. At this time, there is no relation between the rotation velocity of the cylindrical case and the size of the lifting force generated by the lifting force generating elements 181a, 181b. Therefore, a large force may be obtained by rotating the cylindrical case at a high speed.

According to the size of the lifting force and the size of the rotation radius, the size of the generated force is variable. Therefore, part of the generated force may be used for operating the lifting force generating elements 181a, 181b and the remaining force may be utilized for other purpose .

INDUSTRIAL APPLICABILITY

As described hereinabove, the apparatus according to the present invention operates by the force generated in the apparatus itself, continuing the generation of the force, so that any external power supply is necessary. Further, since no external energy source is added, the environmental pollution is not induced and the smallizing the size and volume of the apparatus may be achieved. The force generated by the apparatus may be utilized as not only the power or electricity, but also the engine for air planes, ships and vehicles. Further, the lifting force generating apparatus of the present invention may be utilized for taking off or landing the air planes vertically, reducing the safety accidents of the air planes.

While the present invention has been described in detail with reference to the preferred embodiments, those skilled in the art will appreciate that various modifications and substitutions can be made thereto without departing from the spirit and scope of the present invention as set forth in the appended claims .

Claims

WHAT IS CLAIMED IS ;

1. An apparatus for generating motive force, lifting force and propulsive force, comprising: a fluid compression unit and a turbine unit mounted for rotating in the same direction; wherein the compression unit rotates by an initial power supply from an outside for generating a velocity and a pressure to a fluid to operate the turbine unit for obtaining force; wherein the force obtained by the turbine unit is larger than an energy of the fluid, which is reduced by operating the turbine unit, and the compression unit operates further by the force obtained by the turbine unit; the fluid discharged after operating the turbine unit is applied with a small force to generate the velocity and the pressure energy to restore the fluid to the state before the fluid operate the turbine unit, so that the force applied to the fluid by the compression unit is smaller than the force obtained by the turbine unit, and the force remained after being supplied to the fluid may be utilized for operating other machines .

2. An apparatus for generating motive force, lifting force and propulsive force, comprising: a fluid compression unit and a turbine unit mounted for rotating in the same direction; wherein the turbine unit is formed of two turbine wings, which rotate in the opposite directions to each other; wherein the compression unit rotates by an initial power supply from an outside for generating a velocity and a pressure to a fluid to operate the turbine unit for obtaining force, so that the fluid passes through flow channels formed between wings of a first turbine wing and is discharged with an increasing velocity, the high speed fluid passes through a second turbine wing which rotates oppositely from the first turbine wing to rotate the second turbine wing, the velocity of the fluid being reduced while a pressure of the fluid being increased in the procedure; wherein the reduced fluid energy is complemented by the fluid compressor unit for restoring the fluid energy to an initial state before the fluid rotates the turbine unit; wherein the first turbine wing is formed in the structure similar to an axial flow reaction type turbine with wings which are formed straightly long and thin to pass through the fluid, and flow channels of which sectional areas are uniform for reducing a friction loss of the fluid when the wings are rotating, and the second turbine wing is formed in the structure that the wings of the axial flow reaction type turbine are mounted reversely; and wherein the high speed fluid discharged from the first turbine wing passes through the flow channels between the second turbine wing, the velocity of the fluid becomes reduced while the pressure of the fluid becomes increased in this procedure, and the reduction of the motion energy of the fluid is very small since the fluid operates the turbine unit, generating the force and cooling the fluid.

3. An apparatus for generating motive force, lifting force and propulsive force, comprising: a rotation cylindrical case; a plurality of wing pieces symmetrically mounted to a part of an inner circumference of the cylindrical case with radius of curvature, which becomes reduced gradually; a plurality of rollers symmetrically mounted in the cylindrical case rotatably; and roller supporting shafts inclined slightly with respect to the normal line direction and mounted perpendicularly to inner surfaces of the wing pieces where the radius of curvature is smaller; wherein if an inner cylindrical case rotates, the rollers rotate in contact with the inner surfaces of the wing pieces, generating a centrifugal force to apply a pressure to the wing pieces, so that the cylindrical case mounted with the wing pieces may obtain a torque .

4. An apparatus for generating motive force, lifting force and propulsive force, comprising: a cylinder mounted at a lower part of a vertically vibrating piston and filled with a liquid, the cylinder being formed with holes on a side surface to inflow or outflow the liquid, tubes or elastic elements filled with gas and mounted in the cylinder by a uniform interval for separating the liquid into multiple stages while preventing the flowing of the liquid between the stages; and tubes or elastic elements mounted in outer spaces of the cylinder for separating the outer space into multiple stages; wherein as the piston moves vertically at a high speed, the motion amount of the piston is transmitted to the liquid and the tubes in the multiple stages for generating waves, a pressure of the liquid is periodically changed, the liquid inflows or outflows via the holes of the cylinder according to the change of pressure, the motion amount transmitted to a lower part of the cylinder becomes reduced, so that the motion amount transmitted to a bottom part of the cylinder is smaller than the motion amount applied to the liquid by the piston, generating an upward lifting force.

5. An apparatus for generating motive force, lifting force and propulsive force, comprising: two steel elements mounted perpendicularly to each other for transmitting motion amounts to each other, wherein a vertically moving steel element is formed with curved surface at a contact portion to have an angular displacement of 90° in the curved surface from a horizontal position to a vertical position, and a horizontally moving steel element is mounted with a roller, so that the contact portions of the two steel elements roll smoothly; motion amount absorbing elements respectively mounted to the steel elements for absorbing the motion amounts of the steel elements; a reciprocating electric motor of which a rotation shaft is connected to the horizontally moving steel element; and a vertically moving electric motor of which a rotation shaft is connected to the vertically moving steel element; wherein an upward lifting force is generated in the whole apparatus by an impact amount, which is applied by the vertically moving steel element upwardly.

6. An apparatus according to claim 1, wherein the turbine wing is mounted with a small angular difference with a rotation direction and formed of more than two wings mounted spirally, wherein the wings are thin and long, flow channels between the wings are formed in the shape of spire, an angle between the flow channels between the wings and the rotation direction of the wings is small, a difference between the flow channel direction (fluid outlet) at rear end parts of the wings and the rotation direction is minimum, and a sectional area of the flow channels is proportional to a velocity of the rotation of the wings but inversely proportional to a relative velocity between the fluid and the wings, so that the fluid is introduced in centripetal direction from outer parts of the wings.

7. An apparatus according to claim 1, wherein the turbine wing is formed short and mounted with a small angular difference with a rotation direction and the front end parts of the wings, an angular difference between rear end parts of the wings and the rotation direction of the wings is large, and flow channels between the wings are formed in the shape of curve with a sectional area of the flow channels is rapidly expanded from the front end parts of the wings to the rear end parts, so that the fluid is discharged with a large angle change in the flow channels between the wings .

8. An apparatus according to claim 1, wherein the compression wing unit is mounted with curved wings with a small angular difference from the rotation direction of the wings, and a sectional area of the flow channels between the wings is gradually expanded from the front end parts of the wings to the rear end parts.

9. An apparatus according to claim 1, wherein the compression wing unit is mounted with straight wings with a small angular difference from the rotation direction of the wings, and a sectional area of the flow channels between the wings is gradually expanded from the front end parts of the wings to the rear end parts.

10. An apparatus according to claim 1, wherein the compression wing unit is formed in the axial flow type and mounted with straight wings with a small angular difference from a rotation angle of the wings, and a sectional area of the flow channels between the wings is gradually expanded from the front end parts of the wings to the rear end parts .

11. An apparatus according to claim 1 , wherein the turbine wing unit is structured that velocity component of the fluid works while flowing toward perpendicularly to the rotation direction of the wings

(similarly to the structure of low speed wind mill or water mill) and the mounting angle of the wings is large for the low speed rotation, and the compression wing unit is structured equally to the turbine wing structure, so that the velocity component of the fluid works while flowing toward perpendicularly to the rotation direction of the wings (similarly to the structure of wings of a high speed wind mill) , but the mounting angle of the wings is small for the high speed rotatio .

12. An apparatus according to claim 1, wherein the turbine wing unit is formed in the structure that the velocity component of the fluid forwards perpendicularly to the rotation direction of the wings (similarly to the wing structure of low speed wind mill or water mill) and the mounting angle of the wings is large for the low speed rotation, the compression wing unit is formed in the structure that straight or curved wings are mounted with a small angular difference from the rotation direction of the wings and the sectional area of the flow channels between the wings is gradually expanded from the front end parts of the wings to the rear end parts, and guide wings are further provided for increasing the velocity component of the fluid in the rotation direction of the compression wings and forwarding the velocity component of the fluid in the perpendicular direction of the rotation direction of the wings by correcting the direction of the fluid, wherein a sectional area of the flow channels between the guiding wings is uniform for preventing the reduction of the velocity component of the fluid.

13. An apparatus according to claim 1, wherein guiding wings in addition serving as turbine wings are mounted in addition to the turbine wings unit and the compression wing unit for transmitting the force by the turbine wing unit , the compression wing unit and a power transmission unit to one another, wherein the turbine wing unit is formed in the structure that the velocity component of the fluid forwards perpendicularly to the rotation direction of the wings to work (similarly to the structure of low speed wind mill or water mill) , the guiding/turbine wings are formed in the structure that an angle between front ends of the wings and the rotation direction is small and an angle is largely converted in the flow channels between the wings so as to rotate to convert the direction of the fluid for increasing the velocity component of the fluid in the rotation direction of the wings and the perpendicular direction thereof, and the compression wing unit is formed in the structure that an angular difference from the rotation direction is small and the flow channels between the wings are gradually expanded, wherein the fluid circulates the two turbine wing unit an the compression wing unit.

14. An apparatus according to claim 8, claim 9, claim 10 or claim 12, wherein the sectional areas of the flow channels between the compression wings are gradually expanded from the front end parts to the rear end parts of the wings and the expansion ratio is very small for rotating the wings fast.