US20010012742A1

US20010012742A1 - Propulsion system and method

Info

Publication number: US20010012742A1
Application number: US09/741,102
Authority: US
Inventors: Vladimir Kabakov
Original assignee: Individual
Current assignee: Individual
Priority date: 2000-01-10
Filing date: 2000-12-21
Publication date: 2001-08-09
Anticipated expiration: 2020-01-10
Also published as: AU2001272921A1; US6352458B2; WO2002008054A1

Abstract

A method and system for developing a propulsive force which can be utilized for driving different types of water, air or land vehicles. The propulsive force is developed by rotating a driving shaft with four blades which are simultaneously rotated with the same speed around two perpendicular intercrossed axes in different directions not interfering with each other. Each blade lies generally in a plane perpendicular to the intercrossed axis around which it is rotated. Preferably, the blades have airfoil sections. During such double rotation the radial extensions of the propeller blades relative to the driving shaft are changed as a function of the angle of rotation. The rotated blades can work simultaneously both in a paddling manner and as a screw propeller with the angle of incidence of each of the blades in the plane of rotation around an intercrossed axis changed automatically depending on the position of the blade relative to the driving shaft. The propulsion system can include two or more parallel driving shafts rotated in opposite directions. In a preferred embodiment of the propulsion apparatus the hollow driving shafts are rotated together with planetary gear-boxes mounted thereon and the blades are constrained by planetary gear engagements to rotate synchronously around the axis of the driving shaft and around the intercrossed axes. The planetary gear-boxes can be filled with a lubricating oil.

Description

BACKGROUND OF THE INVENTION

1. Cross-reference to Related Applications [0001]
The present application is a continuation-in-part of application Ser. No. 09/620532 filed on Jul. 20, 2000 which is a continuation-in-part of application Ser. No. 09/479,891 filed on Jan. 10, 2000 which are copending. [0002]

2. Field of the Invention

This invention relates generally to improvements in propeller systems, and more particularly it pertains to a new method and system for developing a propulsive force in a gaseous or liquid fluid and can be used for propulsion or sustaining aircraft, marine vessels, and different types of land vehicles, such for example, as snowmobiles, etc. Numerous other applications can be derived from the use of this invention, for example in designing apparatus for moving gaseous or liquid fluids such as fans, pumps. etc.

3. Description of the Prior Art

Historically, various propeller or paddler systems have been developed for propulsion of different types of vehicles by movement of water or air in opposite direction to the movement of the vehicle. Numerous patents and researches have been devoted to development such propulsion systems wherein the blades are pivoted simultaneously with rotation of the propeller shaft and to the problem of optimizing such cyclic variations of the orientation of individual blades.

Some of such systems utilize rotation of propeller blades or paddles not only around the axis of the driving shaft but also around a complementary axes of rotation for more effective exerting propulsive force. The basic concepts presented in these systems is that the usable propulsive force is developed as a result of rotating the blades around two axes of rotation with variable orientation of the rotated blades relative to the driving shaft.

Propulsion apparatus are known (U.S. Pat. Nos. 1,284,282 to Fitzpatrick, 1,450,454 to Roney, 1,667,140 to Clark, 1923,249 to Abram) wherein blades of feathering type extend radially from the driving shaft and are rotated around radial axes simultaneously with rotation of the driving shaft. In the peddling position the blades are held in a plane parallel to the axis of the diving shaft. In feathering position, the blades are held in a plane perpendicular to the axis of the driving shaft. A serious drawback of such systems is that in the process of changing from one position to the other the blades have to be rotated 90 degrees around their longitudinal axes with a considerable resistance of the fluid and low paddling and propulsion efficiency during such rotation. That is why such systems have low propulsion efficiency in comparison with a screw type propellers.

There are also known propulsion apparatus wherein the propeller blades are oriented and rotated in the planes parallel to the driving shaft (U.S. Pat. No. 3,270,820 to Frazier, British patent No. 217,223 to Pensovecchio). Although having advantages in respect to the propellers with feathering blades, such apparatus with only two blades mounted in a plane perpendicular to the propeller shaft have also low efficiency and irregular power consumption. Different combinations of such propulsion apparatus are cumbersome and the mechanisms employed to effect their operations are far too complicated to render them practical. For these reasons, a limited success has been obtained by such type of apparatus.

The invention seeks to overcome the deficiencies of known propulsion systems and to benefit from the advantages that may be expected from the new method and system.

The object of the invention is to provide a reliable propulsion system for marine vessels, aircraft and land vehicles with improved propulsion and energy efficiency.

BRIEF SUMMARY OF THE INVENTION

The invention is based on my discovery that an effective propulsive force in a liquid or gaseous fluid can be developed by rotating a driving shaft with four blades which are simultaneously rotated around two intercrossed axes which are perpendicular to each other in a plane perpendicular to the driving shaft. Such double rotated blades can be used both as paddling blades and as a screw propeller.

The blades are oriented so that they are always held in planes perpendicular to the axes around which they are rotated. Preferably the blades have airfoil sections. They are connected with the driving shaft and with each other in such a way that when two parallel blades, rotated around one of the intercrossed axis, are oriented along the axis of the driving shaft in opposite directions, the other two parallel blades which are rotated around the other of the intercrossed axis are oriented in the direction perpendicular to the driving shaft. It was discovered that it is possible to rotate four such blades around perpendicular intercrossed axes without interfering with each other if each two adjacent blades mounted in perpendicular planes are rotated in different directions (clockwise and counterclockwise) with the same speed. During such rotations the radial extensions of the blades relative to the driving shaft are changed as a function of the angle of rotation so that they work in a paddling manner virtually during all 360 degrees of rotation of the driving shaft with both sides of the blades being used consecutively as paddling surfaces.

If the rotated blades are mounted with angles of incidence in the planes of rotation around the radial axes, they can work as a double screw propeller simultaneously with the paddling process. Because the orientations of the blades are constantly changed, the angles of incidence of them must be variable.

The propulsion system can include two or more parallel driving shafts rotated synchronously in opposite directions for developing a unidirectional propulsive force. It is possible to mount the driving shafts in a close proximity to each other or/and to a driven vehicle by the sides where the rotated blades are parallel to the diving shaft.

In a preferred embodiment of the invention a gear-box is mounted on each of the driving shaft. The gear-box comprises engagements of planetary angle mitre gears and four radial shafts on which the blades are mounted. During the rotation of the driving shaft the blades are constrained by the planetary gear engagements to rotate with the same speed around the intercrossed axes of the radial shafts.

If the blades work not only in a paddling manner but also as a screw propeller they are mounted on the radial shafts with ability to swing around the axes which are perpendicular to these shafts. Four circular cams are mounted coaxially with the radial shafts and a couple of follower are fixed to each of the blades. The cams are profiled so that the blades swing during of the rotation and their angles of incidence are changed depending on the position of the blade relative to the driving shaft.

BRIEF DESCRIPTION OF THE DRAWINGS

The objects and features of the present invention will become apparent from the following description taken in conjunction with the preferred embodiments thereof with reference to the accompanying drawings, in which: [0018]
FIG. 1 is a schematic view from the stern of a boat with a preferred embodiment of the propulsion system and a fragmentary cross-section on the lines [0019] 1-1 of FIG. 2.
FIG. 2 is a cross-sectional view on the lines [0020] 2-2 of FIG. 1.
FIG. 3 is a schematic fragmentary cross-sectional top plan view on a boat with a preferred embodiment of the propulsion system on the lines [0021] 3-3 of FIG. 1.
FIG. 4 schematically illustrates another embodiment of the of the propulsion apparatus with the blades mounted on the radial shafts with variable angles of incidence. [0022]
FIG. 5 is a cross-sectional view on the lines [0023] 5-5 of FIG. 4.
FIG. 6 is a cross-sectional view on the lines [0024] 6-6 of FIG. 4.
FIG. 7 is a schematic fragmentary cross-sectional view from the stern of a boat with another embodiment of propulsion system with the driving shafts mounted on both sides of the boat. [0025]
FIG. 8 is a cross-sectional view on lines [0026] 8-8 of FIG. 9 of a propulsion system for a marine vessel with an alternative design of the gear-boxes.
FIG. 9 is a cross-sectional view on the lines [0027] 9-9 of FIG. 8
FIG. 10 is a schematic view from the stern of a boat with another embodiment of the propulsion system having a fragmentary cross-section on the lines [0028] 10-10 of FIG. 11.
FIG. 11 is a cross-sectional view on the lines [0029] 11-11 in FIG. 10.
FIG. 12 is a schematic cross-sectional side elevation view of a vertical takeoff and landing aircraft with a propulsion system of the preferred embodiment on the lines [0030] 12-12 of FIG. 13.
FIG. 13 is a schematic fragmentary cross-sectional top plan view on the lines [0031] 13-13 of FIG. 12.

DETAILED DESCRIPTION OF THE INVENTION

The invented marine propulsion systems can be used as an outboard motor application (FIGS, [0032] 1-3) or as stern drive applications (FIGS. 7, 10, 11), where the engine is enclosed within the hull of a boat 10 and the propulsion apparatus are mounted on a unit attached to the transom. Identical details have the same indications in different embodiments.
The propulsion system illustrated in FIGS. [0033] 1-3 includes two hollow driving shafts 11 which are rotatably mounted in housings 12 and can be rotated in opposite directions by an engine 13 through gear engagements 14, 15 (or any other type of drive). Planetary gear-boxes 16 are mounted on the hollow driving shafts 11. An axial support means 17 which is fixed coaxially to the hollow driving shaft 11. Each gear-box 16 comprises four radial shafts 18, 19, 20 and 21 which are perpendicular to each other in a plane perpendicular to the axis of the driving shaft 11. Each of the radial shafts can be rotated in two bearings, one of which (22, 23, 24 or 25) is mounted in the wall of the gear-box and another in the central part of the gear-box (not shown). Two sun angle mitre gears 26 and 27 are mounted on the axial support means 17. Two planet angle mitre gears 28 and 29 are mounted on the radial shafts 18 and 19, respectively, so that they are engaged with the sun angle mitre gear 26. Another two planet angle mitre gears 30 and 31 are mounted on the radial shafts 20 and 21, respectively, and are engaged with the sun angle mitre gear 27. The planetary gear-boxes 16 can be filled with a lubricating oil.
[0034] Blades 32, 33, 34 and 35 are mounted on the ends of radial shafts 18, 19, 20 and 21, respectively, so that each of these blades is generally lying in a plane perpendicular to the axis of the radial shaft on which it is mounted. The blades are oriented in such a way that when two of them (34 and 35) extend in the same direction perpendicular to the driving shaft 11, the other two blades (32 and 33) extend in opposite directions parallel to the driving shaft 11. Preferably, the blades 32, 33, 34, 35 have airfoil sections.
In operation, the [0035] planetary gear boxes 16 are rotated together with the blades 32, 33, 34, 35 in the directions indicated by arrows A and B (FIG. 3). Simultaneously, the blades 32, 33, 34, 35 are constrained by the planetary engagements of angle mitre gears 26, 28, 29 and 27, 30, 31 to rotate around the intercrossed axes of the radial shafts 18, 19, 20, 21 with the speed of rotation of the hollow driving shafts 11. The blades adjacent to each other in the perpendicular planes are rotated in opposite directions (clockwise and counterclockwise) not interfering with each other. As a result of such double rotation, the blades operate in a paddling fashion with their radial extensions relative to the axis of the hollow driving shaft being changed as a function of the angle of rotation. The blades 34, 35 which are in a horizontal paddling position perpendicular to the longitudinal axis of the boat 10 have the maximum extensions and the biggest swept surface, while the other two propeller blades 32, 33 are in vertical positions parallel to the driving shafts 11 in the planes parallel to the longitudinal axis of the boat. After next 90 degrees of rotation of the driving shafts 11 the blades 32, 33 come to the horizontal positions perpendicular to the longitudinal axis of the boat and the other two blades 34, 35 come to the vertical positions (not shown). The positions of the blades after 45 degrees of rotation of the driving shaft is shown in dashed lines.
Because the [0036] blades 32, 33, 34, 35 are rotated around horizontal axes by radial shafts 18, 19, 20, 21, respectively, in opposite directions indicated by the arrows C, D, E, F, they can be used as the blades of a screw propeller. For this purpose, the blades can be mounted with angles of incidence in the planes of rotation around the horizontal axes. Because the orientations of the blades relative to the longitudinal axis of the boat 10 are changed in the process of paddling with both surfaces of the blades used consecutively for paddling, the angles of incidence of the blades must be variable. For this purpose, each of the blades is mounted on the radial shaft with ability to swing in the bearings 36 around the axis 37 which is fixed to the radial shaft in perpendicular direction, as illustrated in FIGS. 4-6. Four circular cams 38 are mounted on the gear-boxes 16 coaxially to the radial shafts 18, 19, 20, 21 and the followers 39, 40 are fixed to each of the blades. The cams 38 are profiled so that during the rotation of the radial shafts the angles of incidence of the blades are changed in accordance with the positions of the blades. In vertical positions the angles of incidence of the blades (32, 33) are zero. When the blades (34, 35) extend perpendicular to the longitudinal axis of the boat, the angles of incidence are maximum.
In the propulsion system shown in FIG. 7, two [0037] vertical driving shafts 11 are mounted on both sides of the boat 10. They are rotated in opposite direction by an engine 41 through pulleys 42, 43, belting 44, a shaft 45 and gear engagements 14, 15. The engine 41 can be mounted in the hull of the boat.
FIGS. 8 and 9 illustrate a propulsion system with a different design of the rotated planetary gear-[0038] boxes 16. Four angle mitre gears 46, 47, 48 and 49 which are engaged with each other, are mounted in the gear-box 16 on the radial shafts 18, 19, 20 and 21, respectively. Two planet angle mitre gears 50, 51 are mounted on the radial shafts 18 and 19, respectively, so that they are engaged with the sun angle mitre gear 52 which is fixed on the axial support means 17. Each of the radial shafts 18, 19, 20, 21 is rotatably mounted in two bearings, one of which (22, 23, 24 or 25) is mounted in the wall of the gear-box 16 and another bearing is mounted in the central bearing support 53. In operation, the rotation of the gear-box 16 is transmitted to the rotation of the blades 32, 33, 34, 35 by the planetary engagements of the gears 52, 50, 51 and by four engaged gears 46, 47, 48, 49.
An alternative embodiment of the propulsion apparatus for a [0039] marine vessel 54 is illustrated in FIGS. 10, 11. A horizontal hollow driving shaft, which consists of two parts 55 and 56 with a gear-box 57 fixed between them, is mounted in the housings 58 and 59 perpendicular to the longitudinal axis of the vessel 54. The design of the planetary gear-box 57 is essentially similar to the designs of the gear-boxes 16 in the embodiments of the propulsion apparatus as shown in FIGS. 1-9. A support means 17 which is fixed coaxially to the hollow driving shaft on the both sides to the vessel 54 and two sun angle mitre gears 26 and 27 are mounted on it, which are engaged with the planet angle mitre gears 28, 29 and 30, 31, respectively.
In operation, the hollow driving shaft is rotated together with the gear-[0040] box 57 and the blades 32, 33, 34, 35 by an engine 60 through pulleys 61, 62 and a belting 63 (or any other type of drive) in the direction indicated by arrow G. Simultaneously, the blades are rotated with the same speed around the axes of radial shafts. As a result of such double rotation, the blades work in a paddling manner in the vertical plane with the maximum propulsion force being exerted in a direction astern when the blades are in vertical positions.
Referring now to FIGS. 12 and 13, a vertical takeoff and landing aircraft is schematically shown. A propulsion system includes two hollow driving shafts mounted on the both sides of the [0041] fuselage 64 of the aircraft parallel to its longitudinal axis. Each of the driving shafts consists of two parts 67 and 68 which are mounted in the housings 65, 66 with a planetary gear-boxes 69 between them. Two sun angle mitre gears 70, 71 are mounted on an axial support means 72 in each of the gear-boxes 69 and the planet angle mitre gears 73, 74, 75, 76 are mounted on the radial shafts 77, 78, 79, 80, respectively. The blades 81, 82, 83 and 84 are mounted on the ends of these radial shafts so that when the blades 81 and 82 are oriented along the longitudinal axis of the aircraft the blades 83 and 84 extend sidewards in horizontal directions from the aircraft.
In operation, the hollow driving shafts are rotated together with planetary gear-[0042] boxes 69 synchronously in opposite directions, indicated by arrows H and K, by the engines 85 and 86 through the gear engagements 87, 88 and the blades on each side of the fuselage 64 are working as “flapping wings”. As a result, a vertical propulsive force is exerted for lifting or sustaining the aircraft. The blades have airfoil cross-sections so that when the aircraft is moving ahead by any other type of propeller or jet engine (not shown) the blades in horizontal positions can be used as regular wings:
While this invention has been described with reference to the structures disclosed herein, the preferred embodiments of the present invention illustrated in FIGS. [0043] 1-13 are not confined to the details as set forth and are not intended to be exhaustive or to limit the invention to the precise form disclosed. They are merely chosen and described to illustrate the principle, applications, and practical use of the invention to thereby better enable others skilled in the art to utilize the invention. This application is intended to cover any modifications of the invention, which may be variously practiced within the scope of the following claims or their legal equivalents, rather than by examples given.

Claims

What is claimed is:

1. A method of developing a propulsive force in a liquid or a gaseous fluid for driving a vehicle, including:

mounting at least one driving shaft on said vehicle;

mounting four blades on said driving shaft with each of said blades lying generally in a plane perpendicular to one of intercrossed axes and with the ability to be rotated around said intercrossed axes, wherein:

said intercrossed axes of rotation being perpendicular to each other in a plane perpendicular to the axis of said driving shaft;

said four blades being constrained by said driving shaft and oriented relative to said driving shaft so that when two of said blades extend in opposite directions parallel to the axis of said driving shaft, the other two blades extend parallel to each other in a direction perpendicular to said driving shaft;

rotating said driving shaft together with said blades around the axis of said driving shaft;

rotating said blades around said intercrossed axes with the speed of rotation of said driving shaft so that when one said blade is rotated clockwise an adjacent blade is rotated counterclockwise in the perpendicular plane so that said blades do not interfere with each other.

2. The method of developing a propulsive force of

claim 1

, wherein said blades are mounted with variable angles of incidence in the planes of rotations around said intercrossed axes and work simultaneously in a paddling manner and as the blades of a screw propeller.

3. The method of developing a propulsive force of

claim 2

, wherein said variable angles of incidence are changed depending on the position of said blades relative to said driving shaft.

4. The method of developing a propulsive force of

claim 1

, wherein at least two said driving shafts are mounted on said vehicle generally parallel to each other and are rotated in opposite directions.

5. A propulsion apparatus comprising:

at least one hollow driving shaft;

a planetary gear-box fixed on said driving shaft;

four radial shafts mounted in said planetary gear-box along said intercrossed axes;

at least one sun angle mitre gear fixed coaxially with said hollow driving shaft in said planetary gear-box;

at least one planet angle mitre gear mounted on said radial shaft and engaged with said sun angle mitre gear in said planetary gear-box;

blades mounted on said radial shafts with each of said blade lying generally in a plane perpendicular to the axis of said radial shaft on which said bade is mounted, said blades being oriented so that when two of said blades extend parallel to the axis of said driving shaft in opposite directions, the other two of said blades are parallel to each other and extend in the direction perpendicular to said hollow driving shaft;

means for rotating said hollow driving shaft.

6. The propulsion apparatus of

claim 5

, wherein two sun angle mitre gears are fixed coaxially with said hollow driving shaft and engaged with said planet angle mitre gears.

7. The propulsion apparatus of

claim 5

, wherein four said angle mitre gears mounted on said radial shafts are engaged with each other.

8. The propulsion apparatus of

claim 5

, wherein:

at least two of said driving shafts are mounted parallel to each other with the ability to rotate in opposite directions.

9. The propulsion apparatus of

claim 8

, wherein there is means for synchronization of rotation of said driving shafts in opposite directions.

10. The propulsion apparatus of

claim 5

wherein said blades have airfoil sections.

11. The propulsion apparatus of

claim 5

, wherein said blades have variable angles of incidence in the planes of rotation around the axes of said radial shafts.

12. The propulsion apparatus of

claim 11

, comprising a means for changing said variable angles of incidence depending on positions of said blades relative to said driving shaft.

13. The propulsion apparatus of

claim 12

wherein said means for changing said variable angles of incidence include circular cams mounted on said gear boxes.

14. A vehicle with at least one propulsion apparatus of

claim 5

.

15. The vehicle of

claim 14

, wherein said vehicle is a marine vessel.

16. The vehicle of

claim 14

, wherein said vehicle is an aircraft.

17. The vehicle of

claim 16

, wherein said blades in horizontal positions are used as regular wings for said aircraft.