THE MULTI-UNIT ROTOR BLADE SYSTEM INTEGRATED WIND TURBINE

Abstract: The described wind turbine has a set of propeller type wind force collecting rotor turbines which is comprised of an up-wind auxiliary rotor blade turbine, being disposed on the front end of the combined bevel-planet gear assembly, and a down-wind main rotor blade turbine. These rotor blades rotate in opposite directions with respect to one another, and the extender enables the main turbine to be activated by normal wind speed without any aerodynamic wake turbulence effects created by the movement of the auxiliary rotor blade. The super-large scale, integrated, multi-unit rotor blade wind turbine has four sets of wind force collecting rotor blade turbines composed of an auxiliary down-wind rotor turbine and three up-wind rotor turbine units evenly spaced around a central pivotal rotor hub on extenders which are the same length as the radius of the auxiliary turbine blade. The above described wind turbines are provided with a microprocessor pitch control system thereby achieving high efficiency operation and to stall for storm control.

Description: DESCRIPTION THE MULTI-UNIT ROTOR BLADE SYSTEM INTEGRATED WIND TURBINE Technical Field The present invention converts natural wind energy into electrical energy by increasing the speed of input rpm in a highly efficient integrated bevel-planet gear box, and through the multi-unit rotary blade system using a propeller-type wind mill generator. Background Art Wind is one of the oldest forms of energy used by man. With enormous increases in demand for environmentally friendly sources of energy, plus a growing fossil-fuel shortage, development of alternative energy sources has been stimulated. In this same environment, wind conversion systems are becoming more efficient and competitive, generating amounts of electrical energy large enough for commercial use. However, in order to meet global clean energy needs, it will be necessary to adopt a new approach to wind-generated electrical energy production. There are two major challenges to a developer of a wind energy conversion system: overall energy conversion efficiency and fluctuations in wind speed and direction. The lower potential power output of wind energy dictates that an advanced conversion system must be of considerable size if substantial amounts of electrical power are to be generated. Taking the above matter into account, the present invention provides a more efficient and improved system which is based on the Prior Art system patented in Korea under No. 0575858 and in the United States under No. 5222924. After experimental field testing, it has become apparent that the counter-rotation of the main and auxiliary rotor blades of the Prior Art in the wind turbine system (FIG. 15) has some need of improvement. For example, the main rotor blade is disposed in the front in an up-wind position, while the auxiliary rotor blade is mounted in a down-wind position functioning as a tail, in order that the wind turbine may face into the wind as the direction varies. However, the up-wind position of the main rotor blade created radius limitations due to the narrow space between the tip of the blade and the tower. Wind blows strongly, the rotor blade was bent toward the tower, finally touching it, with a longer blade bending more easily. And also rotational tip speed is limited with respect to the constraints imposed on the length of the blade's radius. A second structural configuration deficiency needing improvement is the bevel and planet gear box. These sections are separated into an upper bevel gear member and a lower planetary gear member. This design requires a complicated lubrication system as well as extraneous components which curb operational and mechanical efficiency. Disclosure of Invention The present invention is distinguished from the Prior Art in that it is comprised of an improved wind turbine having one auxiliary, these blades are in a counter-rotational relationship, up-wind rotor blade and one main down-wind rotor blade. The up-wind auxiliary blade is positioned in front of the combined bevel and planet gear box, and the down-wind main blade is mounted in the rear, respectively. The radius of auxiliary rotor blade is one-half the lengths of the extender and the main rotor blade radius combined. The two rotational speeds of the main and auxiliary blades have a coincidental tip speed ratio (λ=Vι/Vo, Vo:Wind speed m/s, Vittip speed of rotor blades m/s) which reaches an optimum tip speed ratio independent of wind speed variance. One of the special features of the combined bevel-planet gear device is that the two discrete horizontal input rotational forces of the auxiliary and main rotor turbines are converted into a single higher rotational force which is imparted to the perpendicularly positioned generator located immediately beneath the gear box. Accordingly, the first objective of the present invention is to provide an improved, highly rigid and compact, combined bevel-planet gear assembly, which can convert two rotational forces into one to generated electrical energy throughout the use of a wind turbine disposed on the top of a tower; and to provide a generator system arranged perpendicular to the gear box, whose two horizontal, counter-rotating, input shafts's yielded energy enters the bevel-planet gear box, where they are integrated, and then transmitted to the vertical rotor shaft of the generator. A further objective of the present invention is to avoid aerodynamic wake turbulence effects, such as weakened windstream velocity, through the provision of an extender the same length as the auxiliary blade radius, leading from the rotor hub to the main rotor blade anchor. The wind passes through the auxiliary rotor, activating the main rotor by normal wind velocity alone, without it being disturbed by auxiliary rotor turbine wake. Objective number three of the present invention is to provide a larger area swept by the wind turbine rotor through the inclusion of the wind wall created by both the auxiliary rotor and the main rotor blade. Objective number four of the present invention is to take advantage of this hybrid wind turbine system to function at high rotational speeds as well as at high torques similar to a combination of the American multi-blade low speed, high torque wind turbine and the Danish high speed, low torque wind turbine. Furthermore, several significant advantages are derived from the fact that no yaw control system is required since the system is omnidirectional, i.e., the preferred embodiment of the physical structure of the two rotor turbine system achieves an automatic adjustment to accept the wind from any direction. Also, the variable speed operation means that this wind energy converter system adjusts automatically to changes in wind velocity for maximum efficiency. As a result, rotor speed, blade pitch and optimum tip speed ratio are automatically aligned to obtain the best performance. A function of the electronic pitch control actuator is to act as a stall regulator/storm control device which turns the rotor blades in order to deactivate the generator in the event wind velocity exceeds a level necessary for the safe operation of the system. This represents an ideal solution for interrupting operations of for initiating an emergency stall when necessary, and it is superior to a conventional braking system because it avoids the stresses to the system created by forcible stalling in a mechanical friction brake system. A principal objective of the present invention is to provide an advanced super-large scale wind conversion system consisting of an integrated, multi-unit rotor blade wind turbine system. It is generally known that the conventional large scale wind turbine system has several technical weak points. The first is its rotor diameter limitations. According to to general aerodynamic theory, the output power of a generator is proportional to the square of the sweeping area of the blade. However, restrictions on tip speed of no more than 60 meters per second have been unavoidable because of intensified effects of drag and increased noise pollution. The length of the radius of the rotor blade has also been limited by difficulties in manufacturing longer blades which are aerodynamically balanced. To minimize these obstacles, the present invention integrates a multi-unit rotor blade system to create a super-large wind machine. As shown in FIG 10, it is achieved through the use of three extenders revolving around a main rotor hub, each of which has a rotor blade unit positioned at the apex. The individual rotors rotate clockwise, while the total assembly unit revolves counter clockwise, effectively cancelling the outer motion speed created by the individual rotor blade units. Brief Description of Drawings The aspects, uses and advantages of the present invention will be more fully appreciated as the same becomes better understood through the following detailed descriptions of the accompanying drawings : FIG 1(A) is the front elevational view of the present invention: FIG 1(B) is the side elevational view of the present invention. FIG 2 is a sectional view of the combined bevel-planet gear box assembly of the present invention. FIG 3 is a sectional detail of the FIG 2 illustration. FIG 4 is a detailed view of the section along the A-A line of the bevel-planet gear box assembly presented in FIG 2 . FIG 5 is a detailed view of the section along the C-C line of the bevel-planet gear assembly presented in FIG 2. FIG 6 is a detailed view of the top of the section along the A-A line presented in FIG 2. FIG 7 is an enlargement of the section along the D-D line of FIG2. FIG 8 is an enlargement of detail E in FIG 2. FIG 9 is a sectional view of another functional embodiment of the combined bevel-planet gear assembly of the present invention. FIG 10 s a side elevation of a super-large, integrated, multi-unit rotor blade wind turbine of the present invention. FIG 11 is a front elevation of FIG 10. FIG 12 is a sectional view of the physical structure of the rotor blade system introduced in FIG 9. FIG 13 is a sectional view of physical structure of the main unit turbine illustrated in FIG 12. FIG 14 is a detailed view of the section of the main unit presented in FIG 12. FIG 15 is a side elevation of a conventional wind turbine, a.k.a. Prior Art. Best Mode for Carrying Out the Invention In reference to details regarding the illustrations of the preferred designs of the present invention, i.e., the integrated, multi-unit rotor blade system, as shown in FIG 1(A), FIG 1(B) and FIG 2, it is comprised of : - a main rotor blade(llθ) attached to the rotor turbine(100) - auxiliary rotor blades(201) attached to the rotor turbine(200) - the combined bevel-planet gear assembly(300) - a pitch control actuator(120) for the main rotor blade(110) on the rotor turbine(100) - the differential gear members(130) of the main rotor blade(110) a pitch control actuator(220) for the auxiliary rotor blades(201) on the rotor turbine(200) - a vertical output shaft(420) leading from the combined bevel-planet gear assembly(300) a vertical generator(410), which is mounted within the tower(400) directly beneath the gear box assembly(300) . As shown in FIG 1(B), the up-wind auxiliary rotor blade(210) on the rotor turbine(200) has a radius half length of the extender and main rotor blade(llθ) combined being disposed on the rear end of the gear assembly(300), and it operates in a counter-rotational manner to the main rotor blade(110) at an identical rotational tip speed. This configuration keeps the turbine facing into the prevailing wind at all times. The auxiliary rotor turbine(200) is nearly half size of the main rotor turbine(100) and consists of a three-bladed rotor(210) attached by a shaft(211) to the rotor turbine(200), which rotates at nearly double the speed of the main rotor turbine(100) . The main rotor turbine(100) consists of a three-bladed rotor blade(110) with an extender(111) continuing from the main rotor turbine hub assembly of the combined bevel-planet gear assembly(300) to the anchor point of the main rotor blade(llθ). The length of the extender(111) from the main rotor blade(110) is almost equivalent to the length of the auxiliary rotor blade(210) of auxiliary rotor turbine(200) . This allows the main rotor turbine(100) to perform effectively in normal wind conditions without wake turbulence effects caused by the auxiliary rotor turbine(200) . As shown in FIG 3, the combined bevel-planet gear assembly( 300 ) includes an upper, horizontally-positioned bevel gear(311). This gear(311) is faced by its counter part, a lower bevel gear(312). A plurality of three planet gears(323) are affixed to the inward face of bevel gear(311). A ring gear(322) is rigidly attached to the inward face of bevel gear(312). The planet gear spider consists of planet gears(323) which are attached to bevel gear(311) and a ring gear(322) which is attached to bevel gear(312) inclusively. At the same time, the upper bevel gear(311) and lower bevel gear(312) are perpendicularly disposed in a geared relationship to the vertically positioned bevel gears(313) and (314). The bevel gear(313) is fixed to one end of the input rotary shaft(230) leading from the auxiliary rotor turbine(200) . The bevel gear(314) is fixed to the input rotary shaft(150) of the main rotor turbine(lOO) . Both of these are disposed in a geared relationship to the upper(311) and lower bevel gear(312). Both bevel gear(311) and (312) respond to the main rotor turbine(100) rotation and rotate in the opposite direction at an identical speed from bevel gear(313) and (314), which respond to the auxiliary rotor turbine(200) rotation, respectively. Looking now at both FIG 3 and FIG 6, subsequent to the above described mechanism, the sun gear(321), which is disposed at the center of the planet gear spider, rotates in a geared relationship to the three planet gears(323), which rotate in a respective pivotal axis, revolving around the sun gear(321); while the ring gear(322), which is in a geared relationship with the planet gears(323), rotates in the opposite direction. As described above, the auxiliary rotor turbine(200) and the main rotor turbine(100) energy input is combined in the compact bevel-planet gear assembly(300) device, which is composed of a set of planetary member; three planet gears(323), a ring gear(322), a sun gear(321), and a pair of vertical bevel gears(313) (314), a pair of horizontal bevel gears(311) (312), which are integrated in a "T" shaped gear box assembly. Furthermore, the two low speed input rotary shafts located in the horizontal position are geared into one high speed output rotary shaft located in the vertical position, all within one compact gear box. In reference to detailed illustrations in FIG 3 and FIG 5 , the input rotor hub of the main rotor turbine(lOO) , as diagrammed, is a preferred embodiment of the input differential gear member(130) [see FIG 3] enhancing efficiency, in theory, by a doubling of rpm from the input speed of the main rotor turbine(100) so as to match the tip speed of the auxiliary rotor turbine(200) . The input differential gear member(130) is comprised of a fixed, vertical bevel gear(131) attached to frame(140) [see FIG 3] and an opposing vertical rotating bevel gear(133) which is coupled to the main rotor blade(100) [see FIG 1] of turbine(100) . The input rotary shaft(150) [see FIG 3] extends from the input vertical bevel gear(314) to the three revolving bevel gears(132) [see FIG 3 and FIG 5]. Associated bearings(112), adjusting one end of each extender(lll) of the main rotor blade(110) of the main rotor turbine(lOO), revolve around the fixed bevel gear(131), in gearing with bevel gear(133). This is attached to the input rotary shaft(150) so as to increase the speed of the auxiliary rotor turbine(200) to double the speed of the main rotor turbine(100) both of whose energy input is then imparted to the combined bevel-planet gear assembly(300) [see FIG 3 and FIG 4]. Consequently, the total rotational output number (Zo) of the vertical output rotary shaft(420) [see Fig 1, FIG 3, FIG 9 and FIG 12] attached to combined bevel-planet gear assembly(300) is Zo=(ZS+2ZR/ZS)X 2n, wherein "ZS" represents the number of teeth of sun gear(321), "ZR" represents the number of teeth of ring gear(322) and "n" represents the number of output rotations of main rotor turbine(100) . In FIG 9, an alternate structural embodiment of the present invention is depicted, where the main rotor turbine(lOO) and auxiliary rotor turbine(200) , integrated with the combined bevel-planet gear assembl (300) is consistent with the equation Zo=(ZS+2ZR/ZS)X 2n through the addition of upper horizontal bevel gear(311-1) and lower horizontal bevel gear(312-1) being disposed in the same pivotal axis as bevel gear(311) and (312), and which are in a geared relationship with bevel gear(314-1), which is twice the size of the originally described bevel gear(314). The input rotary shaft(150) connects bevel gear(314-1) to the main rotor blade turbine(100) . The resulting operational performance function of the various gears is exactly the same as that of the input differential bevel gears(130) of the main rotor turbine(100) described in FIG3. Turning now to the side and front elevation views of the super-large scale multi-rotor blade turbine integrated wind conversion system depicted in FIG 10 and FIG 11, it is now in order to describe in detail the component parts and their relationship in both structure and function. The composite wind turbine system of the present invention is intended to provide a super large sweeping area formed by an upwind auxiliary rotor turbine(200) attached to frontend of combined bevel-planet gear assembly(300) along with three upwind multi-unit rotor blade(531) attached to rotor turbine(500) [see FIG 13] mounted on the support hollow extender(511) and input axle shaft(510) of the unit rotor turbine(500) to the input bevel gears(520) and (521), and through extender (511) to the coupled bevel gear(132[132' ] ) of the main rotor hub assembly positioned rear end of combined bevel-planet gear assembly(300) referred to in FIG 12, FIG 13 and FIG 14. The rotational forces of the multi-unit rotor blade(531) of turbine(500) are imparted to the input vertical bevel gears(520), which are in a geared relationship with the horizontal bevel gears(521) [see FIG 13]. The forces are transferred through input axle shaft(510) to the bevel gears(132[132' ] ) [see FIG 12 and FIG 14], which are affixed to the end of input axle shaft(510[lll] ) and which are revolving around the fixed bevel gear(131). The main hub of rotor turbine assembly has the three main multi-unit rotor turbine(500) rotating around the bevel gear(131) which is then coupled to the input rotary shaft(150). Similar functions of operational principles are described here-to-fore in relation to FIG 3 and FIG 9. Maintaining optimum tip speed ratio and a variable running speed in accordance with wind speed variance are the essential factors in a highly efficient wind turbine, especially, the super-large scale wind turbine system where exceeding a high tip speed of more than 60 meters per second in a variable speed wind turbine is unavoidable. Accordingly, as explained above, the linkages within the physical and mechanical structure of the present invention provide for an aerodynamic counter-rotational speed cancellation system through a sequence of orbitally arranged gears which make it possible, by reducing the tip speed of the rotor blades of the super-large scale wind turbine, to achieve the highest energy output efficiency with an optimized tip speed ratio and a low operational noise level. The counter-rotational tip speed cancellation mechanical gear system and principle can be applicable to the main rotor blade of a super-jumbo helicopter. As shown in FIG 11, the rotational direction of unit rotor blade (531) of rotor turbine(500) is in a clockwise direction, while the main rotor hub assembly of the attached supporting extenders(511) leading to the unit rotor turbines(500) are revolving in a counter-clockwise direction. Consequently, when the rotational speeds are identical and the proper configuration of rotational input bevel gears(520), (521), fixed bevel gear(131) and orbital input bevel gears(132[132'] exists, the outward orbital tip speed of the unit rotor blade(531) of rotor turbine (500) is counter balanced by the opposing rotational speed of the supporting extender(511) of the main rotor hub assembly. One of the important features of the present invention is the pitch control feathering mechanism used in both normal and stormy wind conditions. The pitch control actuator(120) of the main rotor blade(llθ) of rotor turbine(lOO), the auxiliary rotor turbine(220) and the control actuator (532) for rotor blade(531) of rotor turbine(500) are feathered independently [see FIG 3, FIG 9, FIG 12 and FIG 13]. This maintains an optimum tip speed ratio during variable wind speed operation. It also initiates a stall mechanism for protecting the structure from danger -during extremely strong wind. Referring to FIG 3, FIG 9, FIG 12 and FIG 13, the pitch control actuators(120) , (220) and (532) are composed of a actuator motor(124), which can be either direction with actuating gear members(123) [see FIG 7] and associated worm gear(122) and worm wheel (121) [see FIG 8] . The main rotor turbine(lOO) and auxiliary rotor turbine(220) are independently controlled by a microprocessor which monitors all wind data through a wind velocity meter and monitors the individual rpm's of both the auxiliary(220) and main turbines(100) so as to keep the same optimum tip speed ratio for all three unit rotor turbines(500) . Detail "E" for FIG 2, as shown enlarged in FIG 7 and FIG 8, illustrated the component parts of the pitch control(120), (220)[see FIG 2] and (532) [see FIG 13] and their relationship operationally and functionally. The first is the start up function whereby the microprocessor adjusts the obtuse angle of the blade, and the blade begins to turn in response to rotatable wind speed being applied for a certain period of time. The actuator motor(124) rotates the activating gear member(123) coincidentally with the worm gears(122) in sync with worm wheels(121) which are affixed to the extended axle shaft of rotor blades(111) and (211) [see FIG 3] and axle shaft(530) of the unit rotor turbine depicted in FIG 13. This adjusts the pitch angle of the blades of the rotor turbine. The second function of the actuator motor(124) is to keep an optimum tip speed ratio in various wind speed conditions by continuously rotating in either direction depending on the control signal received from the microprocessor. The third function is a storm control regulated stall. As exceedingly strong wind forces are applied over the rotor turbines, the storm control mechanism is activated, changing the rotor blade pitch to keep the turbine from turning. Therefore, as illustrated earlier, the emergency stop control operates manually rather than by the use of a mechanical frictional braking system. These functions are performed by preloaded software located in the microprocessor. Numerous modifications and variations of the present invention are possible, such as modifiable single blade rotors, multi-blade rotors, composite individual unit turbines or multi-unit turbines. Also, the rotational direction of the auxiliary and main rotor turbines can be made either counter-rotating or single directional be simply adding gearing devices to either the auxiliary or main rotor turbine. All such modifications are intended to be included within the scope of this present invention as defined by the following claims.

Claims: What is claimed is 1. An apparatus for deriving rotational kinetic energy through multi-unit rotor turbines and an integrated wind mill generator system comprised of a down-wind main rotor blade(110) of rotor turbine (100), including input differential gear member(130) being disposed on the rear of combined bevel-planet gear assembly(300), and an up-wind auxiliary rotor blade(210) of rotor turbine(200) associated with a fixed device pivotally connected to the front of the combined bevel-planet gear assembly(300) . It will catch a certain amount of wind which will assist in the rotation of the main rotor blade(llθ) of rotor turbine(lOO) . These are aerodynamically balanced, counter-rotating at the same tip speed ratio. The combined bevel-planet gear assembl (300) is comprised of a pair of input bevel gear(310) and a set of planetary gear(320) which are mounted on the cylindrical inner space of the four bevel gears(310) respectively. The combined bevel-planet gear assembly(300) effectively increases the rotational force of the two low speed horizontal shafts(150) and (230). It put the gearing process into one mechanical motion of high speed vertical shaft(420) along with output forces imparted to the perpendicularly positioned generators(410) which are mounted on the inside of the tower right under the combined bevel-planet gear assembly(300) and installed on the top of the tower(400) facing -automatically into the wind without need of a active yaw control as the structure of the turbine system makes it aerodynamically possible to do , 2. According to claim 1, the present invention is the down-wind main rotor blades(110) and extenders(111) of the rotor turbine(100) being mounted on the read end of the combined bevel-planet gear assembly(300) which is designed to be rotated by wind. The auxiliary rotor blades(210) of rotor turbine(200), being mounted on the front of the combined bevel-planet gear assembly(300), can assist in the rotation of main rotor blades(110) of the rotor turbine (100) as well as over speed control and starting assistance. These physical arrangements and structural accommodations of the double sized diameter of the main rotor turbine(100) and the half sized diameter of the auxiliary rotor turbine(200) of the multi-unit rotor blade turbine system automatically keep the system facing into the prevailing wind without need for an active yaw control system. 3. In the present invention as set forth in claim 1, the rotational diameter of the auxiliary rotor blade(210) of turbine(200) is almost equivalent to the dimensions of extender(111) of the main rotor turbine(lOO) so that normal wind forces are applied over the down wind main rotor blade(110) of the rotor aerodynamic wake turbine from auxiliary rotor blade(210) of the turbine(200) . 4. An _ apparatus of the present invention as set forth in claim 1 is a differential gear member(130) of the input rotor hub of main rotor turbine(100) further comprising a means, based on the theory of differential gear system, for doubling the rpm from the input speed of the main rotor turbine(100) and in principle, to match the tip speed of the auxiliary rotor blade(210) of the turbine(200) to that of the main rotor turbine(100) . The above said performing differential gear members consist of a vertical bevel gear(131) which is affixed to the frame(140). The bevel gear(131) is against a vertical bevel gear(133) which is coupled in rotation to the main rotor blade(110) and input rotary shaft(150) of the main turbine(lOO) . Three input bevel gears(132) associated with bearing(112) are rotationally mounted on one end of three extenders(111) of the main rotor blade(llθ) of the main rotor turbine(lOO) . These are coupled with rotational bevel gear(133) of the input rotary shaft(150) and are rotating and revolving around in a geared relationship to the fixed bevel gear(131). In accordance with differential gearing principles, the main rotor turbine(100) makes one revolution while the auxiliary rotor turbine(200) makes two revolutions so as to match rotational tip speed of both rotor turbines(100) and (200) aerodynamically. 5. An apparatus of the present invention as set forth in claim 1 is pitch control actuators(120), (220) and (532) for the main rotor blade(100) of the rotor turbine(100) and auxiliary rotor blade(210) of the main rotor blade(110) of the rotor turbine(100) and auxiliary rotor blade(210) of the rotor turbine(200) and main rotor blade(531) of the turbine(500), the pitch control actuators adjust the pitch angle of the blade to take advantage of the wind velocity. Pitch control actuators(120) , (220) and (532) have three functions: start up assistance through the adjustment of the pitch angle of the blades for cut in wind speed, adjusting the pitch angle for an optimum tip speed ratio to achieve maximum efficiency of operation in a given wind velocity, and a stall regulator for storm winds control or emergency stops. 6. An apparatus of the present invention as set forth in claim 5, the pitch control actuators(120), (220) and (532), is a microprocessor controlling the actuator motor(124) including the activating gear members(123) geared with worm gears(122) coupled to worm wheels(121) being a affixed to one end of the extender shaft(lll) of the main rotor turbine(llθ), to one end of the extender shaft(211) of the auxiliary rotor(121) and to one end of extender shaft(530) of the main rotor blade(531) respectively. 7. An apparatus of the present invention as set forth in claim 1 is the combined bevel-planet assembly(300) comprised of an upper bevel gear(311) and a lower bevel gear(312), which are in a geared relationship with a pair of input bevel gear(314) and (313), which are mounted on one end of horizontal rotary shafts(150) and (230). The other end is connected to main rotor turbine(lOO) and auxiliary rotor turbine(200) respectively. An alternative structural embodiment of the combined bevel-planet gear assembly (300) is provided with an additional upper bevel gear(311-1) and lower bevel gear(312-1) which are disposed in a geared relationship with a double sized diameter of bevel with a double sized diameter of bevel gear(314-1) instead of bevel gear(314) being fixed to one end of input rotary shaft(150). The planet gear members(320) located in a central cylindrical space being composed of vertical counter-rotating input bevel gears(314-l) , (313) and a pair of horizontal upper and lower counter-rotating bevel gear, (311) (311-1) and (312) (312-1) respectively. 8. An apparatus of the present invention as set forth in claim 1 and claim 7 is the combined bevel-planet gear assembly(300) , which is a planetary gear spider composed of a set of three planet gears(323) perpendicularly disposed 120 degrees to the upper horizontal bevel gear(311) on the ceiling surface facing downward and a ring gear(322) being perpendicularly disposed to the bottom upwardly facing surface of the lower horizontal bevel gear(312). As a consequence, the said planetary gear spider(311), inclusive of planet gear(323), and the ring gear(312) rotate in opposite directions at an identical speed as planet gear(323) revolves around the centrally positioned sun gear(321) and in so doing, coupling with the surrounding ring gear(322) which rotates in an opposite direction from the sun gear(321) and planet gear(323). As a result, the sun gear(321) has the output vertical rotary shaft(420), which is connected to generator(410), passing through its hollow center and through the lower bevel gear(312). The output rotation of the gear ratio of said combined bevel gear assembly(300) is 1+2ZR/ZS, where ZR represents the number of teeth in the ring gear(322) and where ZS represents the number of teeth in the sun gear(321). 9. An apparatus of the present invention as set forth in claim 1 is the input differential gear member(130) of the main rotor turbine(100) which can be modified to where a simple input bevel gear arrangement is achieved by making the main unit rotor turbine(500) rotate and revolve around the input fixed vertical bevel gear(131) of the rotor turbine(100) . The rotation direction of the three main rotor turbines and their assembly of multi-unit blade systems which are revolving around in an opposite direction with respect to each other on a pivotally centered fixed bevel gear(131) of rotor turbine(lOO) of the super-large scale wind turbine, results in the outward orbital tip speed of the three unit rotor blades(531) of the rotor turbine(500) to be counter-balanced by the revolving speed of supporting extend (511) of the main rotor hub assembly(100) through an arrangement of identical rotating speeds, which is aerodynamically cancellation the speed of rotation of the rotor blades, coupled with the maintenances of optimum tip speed ratio independent of wind speed variance, makes it possible to achieve the most highly efficient variable speed rotor turbine operation. This mechanical gear system and the effect can bee applicable to the main rotor blade wing of a super-large jumbo helicopter. 10. An apparatus of the present invention as set forth in claim 9 is the input bevel gear(132 [132']) which is stably mounted on one end of input rotational axle shaft(510[111] ) being connected on the other end to the input bevel gear(521) which is coupled with bevel gear(520) of the unit rotor turbine(500) respectively, all of which revolve in a geared relationship with the perimeter of said fixed bevel gear (131) of the rotor hub assembly of the super-large scale wind turbine.

Inventors: SHIN CHAN, SHIN, CHAN
Applicants: SHIN CHAN, SHIN, CHAN
Application year: 1995
Main classification: F03D1
IPC codes: F03D1, F03D11