KR20150029666A - propulsive equipments integrated blade and casing and propulsion method using it - Google Patents

Abstract

The present invention can be applied to all propellants, including ships and airplanes, that propel (propel) by using the repulsive force with the surrounding fluid that occurs during the process of increasing the fluid velocity through the rotation of the wing and discharging the fluid to the rear of the propellant. The present invention relates to a new type of propulsion device and a propulsion method using the same. The device includes a rotor, an induction device and a housing, and a rotor support frame. In particular, a rotor includes a cylinder, One or more stationary blades fixed at 90 degrees to the inner surface of the cylinder, a power transmission device including rim gears and sprockets for power transmission and shafts, a support device for supporting the weight of the cylinder, A vibration control device for controlling the vibration, a displacement control device for controlling the displacement of the cylinder, and a leakage preventing device, and the diameter and the length of the cylinder are determined according to the fluid density and the conditions of the propellant A propulsion device in which a wing and a cylinder are integrated and rotated to increase the propulsion efficiency by adjusting the number and height of the wing installed inside the cylinder together with the adjustment angle and the installation length, and a propulsion method using the same.

Description

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a propulsion device having a wing and a casing integrated with each other,

The technical field to which the present invention is applied is the propulsion device manufacturing technology and the operation principle of the propulsion device among the fields related to the propulsion device for propelling (propelling) through the wing rotation.

The rotor type of a propulsion device applied to a conventional ship or a flying body is a type in which a propeller or a screw having several wings individually or integrally connected is connected to a shaft for transmitting rotational force, Is propelled by using the repulsive force generated by discharging the propellant in a direction opposite to the direction of movement of the propellant. However, in this type of rotary vane, the energy conversion with the fluid is completed in a single contact with the blade area and height in contact with the fluid being completed, and the point where the shaft and the blade are connected is located at the rotation center of the blade, Vibration is generated due to fluid congestion and turbulence at the front and back of the center of wing, and the velocity of discharged fluid is reduced and vibration occurs. In order to suppress the displacement, a phenomenon occurs in which the cross-sectional area of the shaft supporting the wing and the supporting frame are increased excessively, and the disturbing flow of the peripheral fluid generated by the opening of the vane end having the greatest rotational force with the fluid, Energy is consumed unnecessarily and energy is consumed in the rotational motion of the discharged fluid, To move to the desired speed and the night air vehicle, the inefficient phenomena such as the use of high-powered engines that can express the real momentum and sustainability while including these unnecessary wasting of energy.

In addition, the propeller used as a propulsion device of a ship has a limitation in increasing the degree of severity, which is formed by the plane perpendicular to the rotation axis and the blade longitudinal surface, and operates in a limited moving range in the open state with the surrounding fluid Accordingly, it is a reality that there is a limit to increase the energy conversion ratio that converts the rotational energy transmitted to the propeller to the linear kinetic energy required for ship movement.

(Patent Document 1) KR0445508 10 "rotor" refers to a rotor and a housing and a duct associated therewith, which are gradually reduced in one direction along a rotating shaft and are formed in a spiral continuous form, This technology reduces turbulence and noise at the same time.

(Patent Document 2) KR0303379 10 "propulsion device for underwater vehicle" refers to a propulsion device composed of a rotary vane, a fixed vane and a duct surrounding the rotary vane, and is characterized in that the propulsion efficiency in water, the reduction of radiated noise, Technology,

(Patent Document 3) KR0700375 10 "Impeller for water jet propulsion device for marine vessel" is designed to install each impeller blade in a twisted shape in order to reduce physical damage, noise, vibration and cavitation of the propulsion system,

(Patent Document 4) KR1152703 10 "Aircraft" refers to an aircraft having two or more hollow cylindrical lifting bodies in the body of an aircraft, a blade capable of adjusting the angle on the outer periphery of the lifting body, The discharge direction of the sucked air is discharged along the direction of opening and closing the blades, thereby enabling vertical takeoff and landing of the aircraft and rotation of the aircraft,

(Patent Document 5) KR0938547 10 "Tilt-duct airplane and attitude control of the airplane" is a method of installing a peeling groove in a duct inside a duct due to inevitable flow separation phenomenon in a tilt-duct air vehicle capable of vertical takeoff and landing and horizontal flight And various controls by the vane installed at the rear of the duct and the duct swinging by the swing angle adjusting unit are enabled and the entire structure is simplified.

However, in the above technique, the "rotor" is gradually reduced in one direction along the shaft, and the operating area of the rotor fixedly mounted on the shaft in a continuous spiral form is uneven and vibration is likely to occur in the shaft. The impeller of the impeller of the propulsion device and the impeller for the water jet propulsion device of the ship are both directly connected to the shaft and rotated, and the airplane is installed inside the hollow cylindrical duct which forms the core of the technology The operation method of the rotor also rotates in connection with the shaft, and the "tilt-duct air vehicle and attitude control of the air vehicle" is a method in which the behavior of the rotary vane rotates in connection with the shaft in the duct, Is the same as that using the rotary blades connected to the shaft, with the above-described limitations being the same.

Patent Document 6: KR1037995 10 "WIG line capable of vertical take-off and landing" is a technique for generating a propulsive force required for floating by a floating duct provided inside a main hull and a propeller installed inside the duct.

(Patent Document 7) KR1137822 10 A "flying object" has a propeller operated by a motor at the upper end portion of the housing, which passes through the upper and lower portions, and various control devices, which are individually operated below, are installed to reduce the total number of actuators required for flying In addition,

(Patent Document 8) KR1205949 10 "Ship propulsion device and ship including the same" refers to a configuration of a double inversion propulsion device in which a first rim connected to a plurality of blade tip portions connected to a main shaft without using a hollow shaft a second rim rotatably disposed in the duct and rotatable in the direction of the main axis within the duct in a state of being separated from the first rim and having a plurality of separate blades and a propeller connected to the rim, The efficiency is improved by installing a bevel gear device to be operated between the rims,

(Patent document 9) KR1282497 10 "Propeller propulsion device in which the curved plate of the propeller is inserted into the groove of the inner surface of the duct" forms a groove in the duct surrounding the propeller blade, and the tip of the propeller blade is rotated in the groove formed in the duct Tip vortex cavitation, flow loss and so on,

(Patent Document 10) KR1313574 10 "Ship propulsion device and ship equipped with the same" relates to a device and a technique for improving the propulsion efficiency by improving the front and rear wing shape and installation method of the double inversion propulsion device.

However, since the propulsion system used in all of the above technologies is a propulsion system using a propeller rotating around a shaft, fundamentally there is a limit to the increase in propulsive force that can be expressed in comparison with the energy to be input.

In addition, KR142269410 "propulsion device for marine vessel" is capable of variably adjusting the pitch of a rotary blade of a thruster used for changing the direction of a ship, thereby reducing cavitation and noise and improving propulsion efficiency Respectively.

(Patent Document 12) KR20120050520 10 "Mechanically driven hub-less high efficiency ship propeller" includes a rotor with a gear rim having a wing inside the ring, which rotates within a duct And wherein the rotating blades of the rotor are each an apparatus and a method for increasing the efficiency in such a manner that the pitch can be adjusted.

However, in the above-mentioned technique, the method of variably adjusting the pitch of the rotating blades of the thruster in the "propulsion device for marine" has limitations in the propulsion efficiency improvement due to the fundamental limitations of the propeller. Quot; high-efficiency ship propeller without "describes only the installation of a plurality of blades on the inner surface of the rotating body without clearly indicating the method of installing the blades installed inside the rim and the rim installed inside the duct And the method of variably adjusting the respective blades is unclear and the behavior occurring between the blades and the fluid can not be clearly understood, and the blade mounting method is differentiated from the present invention.

It is an object of the present invention to overcome the functional limitations and structural limitations of the above-mentioned prior arts and apparatuses and to provide a method of controlling the rotational energy supplied from a power source by a linear motion energy of a fluid through a rotor operation The present invention provides a propulsion device in which a wing and a casing are integrated and a propulsion method using the propulsion device.

In order to solve the above-described problems, the present invention provides a rotor and an induction device for distributing or concentrating a fluid discharged from a cylinder, which is one of the rotor components, A housing in which a rotor is installed, and a rotor supporting frame,

Each of the devices constituting the rotor includes a cylinder having an inlet and an outlet formed as an opening in a fluid flow direction and rotating about a longitudinal axis, At least one stationary blade fixedly installed at an angle of 90 degrees with the inner surface of the cylinder and fixed at the same moving angle, a power transmission device including a power transmission rim gear, a sprocket and a shaft, A displacement control device for controlling the displacement of the cylinder in a direction opposite to the direction of fluid discharge, a displacement control device for controlling the displacement of the cylinder, And the like.

In addition, the housing is installed in a manner to surround the rotor from the outside, and an induction device, a cylinder, a cylindrical support device, a power transmission device, a cylindrical displacement control device, a cylindrical vibration control device leakage prevention device,

In addition, the contour of the housing may be installed in a fluidic geometry to minimize mutual interference with the fluid being applied.

In addition, the induction device is installed inside the housing in a conical shape in which the cross-sectional area is continuously reduced at the front face of the cylinder into which the fluid is introduced, and has a conical shape in which the sectional area is reduced or increased constantly at the rear face of the cylinder in which the fluid flows out. In the housing.

In addition, at least one guide member for dispersing the fluid to be discharged or for reducing the fluid rotational force may be provided inside or outside the induction device when the induction device is installed in a region where the fluid flows out. , A straight line or a ring, or a combination of a straight line and a ring.

In addition, at least one power transmitting device and a supporting structure in which a rim gear, a sprocket, and a shaft for transmitting rotational force are combined may be provided on the outer surface of the cylinder.

In addition, at least one displacement control device for restricting the movement of the cylinder caused by the interaction of the fluid and the fixed blade can be provided on the cylindrical outer surface.

In addition, at least one vibration control device for suppressing the vibration of the cylinder caused by the interaction of the fluid and the fixed vane can be provided on the outer surface of the cylinder.

In addition, the cylinder is provided inside the housing to minimize the contact between the fluid and the cylindrical outer surface.

Further, the cylindrical body is provided inside the structure isolated from the fluid, so that the contact between the fluid and the cylindrical outer surface can be minimized, and maintenance can be facilitated.

In addition, a leak preventing device may be provided on both ends of the cylinder.

In order to rotate a rotor including a cylinder and a cylinder, a bearing or at least one support device which is composed of at least three rollers and which operates and operates at least one position And a fixing frame supporting the supporting frame can be installed together.

Further, the fluid may be air, fresh water, steam or seawater.

In addition, the fixed blade has a helical shape along the inner surface of the cylinder, and can be fixedly installed at least one.

The displacement control device may be constituted by a bearing or a combination of three or more supporting rollers which are operated in a state of being in contact with an iron plate surface for displacement control in the fluid discharge direction, And may be provided on the outer surface of the cylinder, and may be provided with a supporting frame for supporting the rear and lower portions thereof.

The vibration control device includes a vibration control steel plate fixed along the outer circumference of the bearing or cylindrical outer peripheral surface and having a triangular section and a ring shape as a whole, At least two or more rollers may be combined, and at least one or more supporting frames may be provided together.

The present invention can drastically reduce unnecessary energy consumption by the operation principle of the propulsion device,

In addition, the present invention can increase propulsion efficiency by adjusting the number of fixed wings, the height, the moving angle, and the length according to the fluid density, the weight of the propellant, and the maximum velocity of the propellant,

Further, the present invention is a method for adjusting the bending angle of the fixed end and the free end according to the fluid density, the weight of the propellant, and the maximum velocity of the propellant, Can be increased,

In addition, when the present invention is used as a propulsion device for a ship, the propulsion device can be installed inside the ship to increase the life of the propulsion device, facilitate maintenance,

Further, the present invention can be applied to vertical takeoff and landing and horizontal movement of a flying body, reduce noise and air vibration phenomena generated during operation of the propulsion device, and achieve a desired propulsive force with a relatively low fuel consumption amount , Maintenance and operation costs can be minimized.

BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is an explanatory view schematically showing a method of mounting a fixed blade in a cylindrical and cylindrical interior of an induction device, a housing, and a rotor of the present invention, and a method of installing the propulsion device; ,
2 is a schematic explanatory diagram for explaining a mutual behavior between a fixed blade and a fluid in a cylinder of a constituent device of a rotor according to the present invention,
FIG. 3 is a schematic view showing a method of installing and functioning a steel displacement control steel plate, a steel plate for vibration control, and a rim gear for power transmission mounted on a cylinder among constituent devices of a rotor according to the present invention; However,
4 is an explanatory view schematically showing a method of installing a cylindrical vibration control device and a displacement control device among constituent devices of a rotor according to the present invention,
FIG. 5 is a schematic explanatory view showing a cylindrical supporting apparatus and a mounting method thereof, among the constituent devices of a rotor according to the present invention,
FIG. 6 is an explanatory view for explaining a method of installing a propulsion device for vertical take-off and landing and a predicted effect of the propulsion device for vertical takeoff and landing in a flight vehicle that obtains propulsion force using a jet engine or a gas turbine,
FIG. 7 is an explanatory view for explaining a method of installing a propulsion device and a predicted effect according to the present invention in a helicopter, which is one of applications of the present invention.
FIG. 8 is an explanatory view for explaining a method of installing a propulsion device and a predicted effect according to the present invention, which is one of applications of the present invention.

The above and other objects, features and advantages of the present invention will be more apparent from the following detailed description taken in conjunction with the accompanying drawings.

BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is a schematic view illustrating a method of mounting a fixed blade in a cylindrical and cylindrical interior of an induction device, a housing, and a rotor of the present invention, and a method of installing the propulsion device. The apparatus is composed of induction devices 109 and 110, a housing 102, a rotor, and a rotor support frame. The rotor is composed of a cylinder 100 and a fixed blade 101, a cylindrical displacement control device (not shown) (Not shown), a power transmission device (not shown), a cylindrical support device (not shown), a water leakage prevention device (not shown), and the like.

 The cylinder 100 is a circular pipe with an inlet and an outlet open. When the fluid is seawater or land, the cylinder 100 is made of stainless steel, which is resistant to torsion and is resistant to corrosion. And the diameter and length are adjusted according to the constraints such as the density of the fluid, the weight of the propellant and the speed to be achieved, and the fixed blade installation method.

In addition, when the propellant is a lightweight body such as a drone, the cylindrical 100 may be a rigid industrial plastic tube having a high rigidity, and each of the fixed vanes 101, the power transmission device, It can be made of the same material as the cylinder or a light weight metal material.

In addition, at least one of the stationary blades 101 is fixedly mounted on the inner surface of the cylinder, and the example shown in the upper part of Fig. 1 is a case where one stationary blades are installed. It is a schematic diagram.

In order to reduce the friction with the fluid, the fixed blade (101) may be formed so that the free end surface has a sharp shape. In order to increase the friction with the fluid, the wing starting end surface and the end surface are formed to have a sharp shape And can be manufactured such that the blade height gradually increases or decreases for a certain length near the starting point and end point of the blade.

In addition, the fixed vane 101 may be mounted in such a manner that each vane is continuous from the starting position to the end position while maintaining the same moving length and moving angle around the cylindrical rotating shaft on the inner surface of the cylinder.

 The fixed blade 101 is a method of adjusting the number, height, displacement angle and length of blades installed in the cylinder according to the fluid density, the weight of the propellant, and the maximum velocity of the propellant, .

In addition, at the inlet of the cylinder 100, a conical induction device 109 in which the circular cross section is reduced uniformly from the fluid inlet to the cylinder can be provided to increase the fluid inflow speed. In the outlet of the cylinder 100, A similar type of induction device 110 may be provided to properly adjust the flow rate of the outflow.

The cylinder 100 may be installed in the inside of the structure 112 isolated from the outside by the boundary of the wall 111 including the induction devices 109 and 110. As a result, Can minimize direct contact with the fluid and can facilitate maintenance.

In addition, when the propulsion device is installed in the inside of the structure 112 isolated from the outside, the induction devices 109 and 110 may be provided with a fluid shut-off device (not shown) operated in the vertical direction or the left- It is possible to easily refine each of the accessories of the propulsion device.

In addition, the housing 102 has a fixed structure that does not rotate, and an induction device and a rotor may be installed therein.

The housing 102 may be connected to the propellant through a connection with the support frame 802 and the auxiliary support frame 803 through which the shaft passes,

In addition, the housing 102 may be omitted when the propulsion device is installed inside a vessel or a flying body.

  Hereinafter, preferred embodiments of the present invention will be described with reference to the accompanying drawings. Embodiments of the present invention will be described by those skilled in the art to which the present invention is applicable.

Accordingly, the embodiments of the present invention can be modified into various other forms, so that the claims of the present invention are not limited by the embodiments described below.

FIG. 2 is a schematic view for explaining various behaviors that occur in the fluid inside the cylinder as the stationary vane rotates integrally with the cylinder among the constituent devices of the rotor according to the present invention. The change in energy generated in the fluid inside the cylinder due to the integrated rotation of the fixed blade 100 and the fixed blade 101 is such that the energy supplied from the power source is constant regardless of the fluid position energy and the loss energy due to friction Occation,

0.5 × (Meter) × (Rter) × (Water) ² + 0.5 × (M) × (V1) ² = 0.5 × (M) × (V2) (R oil) ² × (W oil) ² + (FE oil)

Can be expressed as a relational expression.

Another meaning of the above expression is that the rotational angular velocity (W factor) when the fluid exits the cylinder 100 is minimized to increase the efficiency of the propulsion device when the weight of the propulsion device and the fluid is calculated at a fixed value The method of reducing the fluid rotational angular velocity (W type) means that the diameter and length of the cylinder are determined by the method of installing the fixed vanes installed in the cylinder and the operation principle of the propulsion device.

Based on the above concept, a method of installing the fixed blade 101 mounted in the cylinder 100 and a method of generating propulsion force using the fixed blade 101 will be briefly described.

In the illustrated example, three fixed blades 101 are respectively installed on the inner surface of a cylinder moving the same distance at the inner surface of the cylinder 100, and the free ends of the blades are always directed to the center of the cross section in the longitudinal direction of the cylinder 100 The wings are installed along the inner surface of the cylinder with the same displacement maintained at an angle of 120 degrees between the wings. The end points of the wings are rotated counterclockwise from the start position by 120 degrees, Installed.

Further, the fluid flowing into the cylinder through the cone-shaped guiding device 109 changes in flow rate in inverse proportion to the cross-sectional area ratio of the inlet and outlet of the induction device.

Further, when the cylinder 100 starts to rotate by the power transmission device, the fluid flowing inside the cylinder rubs against the inner wall of the cylinder and the fixed blade 101, and the fixed end of the fixed blade End) and receives a rotational force that decreases toward the center of the cross-section of the cylinder.

The contact surfaces 204, 205 and 206 for transmitting the rotational force of the fixed blade 101 to the fluid are on the right side of the fixed blade with reference to the cross section viewed from the inlet of the cylinder, And is continuously rotated in the counterclockwise direction in accordance with the distance from the fixed blade. At this time, the fluid in the right space of each stationary blade section rotates counterclockwise due to the behavior of the blade. In addition, the fluid in the left space of each stationary blade section rotates in a counterclockwise direction due to the behavior of the successive leftward stationary blade.

In addition, the fluid in the center of the cylindrical section has a relatively small area in contact with the fixed blade, so that the fluid behaves counterclockwise due to the fluid behavior in the area between the blades,

In addition, as the cylinder and the fixed wing are integrally rotated by the rim gear mounted on the outer surface of the cylinder, the rotation center of the fluid inside the cylindrical longitudinal direction section is the area between the fixed wing free end of the same cross section and the center of the cross- And the disturbance intensity of the fluid generated in this region is very weak,

Further, the phenomenon that the fluid at the central portion of the cylindrical cross section increases in speed due to the action that the fluid in the region between the wings collects at the center portion of the cross section due to the centrifugal force generated by the rotation of the cylinder.

Further, when the cylinder starts to rotate, the entire fluid flow rotates counterclockwise with maximum rotational force in the vicinity of the fixed end where the right side of the fixed blade meets the cylindrical inner surface in the three small regions located between the fixed blades, And the whole fluid in the cylinder rotates counterclockwise.

In addition, the magnitude of the rotational angular velocity generated in the fluid is substantially similar to the entirety due to the effect that the cross-sectional center of the cross section is not clogged by the fixed blade but the cross sectional area of the unblocked portion is not wide, The flow direction of the fluid in the outflow direction expressed by the contact action between the rotating direction surface of the wing and the fluid exhibits a similar magnitude in the entire inner circumference portion provided with the fixed wing.

In addition, the above-described fluid behavior is completely different from the fluid behavior method occurring at the propeller end operated by connecting the center of the shaft and the rotating body. The turbulence intensity generated at the free end of the fixed blade is relatively small, This is a small cause that is much weaker than the turbulence intensity at the tip of the propeller connected to the shaft, and as a result, unnecessary energy consumption can be minimized, resulting in an increase in propulsion efficiency.

In addition, since the fluid flowing in the space on the left side of the section of each fixed blade 101 is the fluid flowing on the right side of the other fixed blade, the above-described behavior is performed in the same manner.

Further, the above-mentioned various behaviors of the fluid occur simultaneously in the whole of the fixed blade, and the energy transmitted from the contact surface of the entire fixed blade by the continuous operation of the fixed blade is changed by the installed shape of the fixed blade, When the energy transmitted from the power source exceeds the sum of the rotational energy required for rotating the propulsion unit and the energy used to move and rotate the fluid inside the cylinder, And moves the fluid. Therefore, when the propulsion system is started for the first time in a stationary state, the required rotational force is greatest. In this case, the specification of the power source is adjusted by controlling the time required for the propulsion system to generate the target revolutions per minute (rpm) Should be.

 In addition, the mutual behavior of the fixed blade 101 started to rotate and the fluid occurs in the same manner as described above. However, as the fixed blade contact surface, to which the fixed blade transmits energy, rotates counterclockwise, The contact point between the fixed blade and the fluid is continuously changed, thereby shortening the contact time with the fixed blade,

In addition, due to the rotation of the cylinder 100 and the fixed blade 101, the flow velocity of the fluid flowing into the cylinder due to the movement of the propellant in the direction opposite to the fluid discharge direction relatively increases, The rate of conversion of the rotational energy supplied to the fluid to the linear kinetic energy of the fluid is increased. As a result, the circulating action such as the increase of the flow rate of the fluid discharged from the cylinder, In addition,

In addition, the above-mentioned increase in the traveling speed of the propellant is determined by the amount of energy supplied from the power source including the size of the rotor and the number of revolutions per minute (rpm), and finally, The flow rate of the propellant increases until energy equilibrium is established between the flowing fluid and the moving propellant.

In addition, depending on the rotational speed of the cylinder 100, the amount of energy consumed for the counterclockwise rotation of the fluid generated during rotation is varied, and the total energy transferred to the fluid by the fixed wing varies The flow rate of the fluid is determined by the energy used for the counterclockwise rotation of the rotor and the residual energy other than the energy consumed by the friction. Therefore, in order to increase the fluid flow rate to be discharged, the higher the rotation speed of the cylinder, excluding the friction, the better the number of the fixed wing installation is, and the larger the fixed wing height is, the better.

In addition, when the moving angle of the fixed blade (101) is made smaller than the unit length of the center line of the cylinder (100), the fluid flow rate increases and the fluid rotation speed can be reduced by a certain amount. Depending on the maximum travel speed to be implemented and the power source to be applied, various combinations are possible between the cylindrical bore and the fixed wing.

In addition, during the above process, vibration and displacement of the cylinder due to contact between the fluid and the stationary vane occur, and the vibration and displacement size are influenced by the fluid density and flow rate, the number of the stationary vanes and the installation height and movement angle, It is affected by length.

In the illustrated example, the three fixed blades 101 are arranged so that the start position and the end position are maintained at the same displacement and are rotated by 120 degrees. When viewed from the inlet of the cylinder 100, This installation method is capable of continuously transferring the rotational energy of the propulsion device to the fluid in the cylinder through the projected area that is closed and providing a uniform, It can be converted into linear kinetic energy.

In addition, when the fixed blade (101) is installed up to the position where the projected area is secondarily closed, the rotational energy of the rotor is converted into the linear kinetic energy of the fluid, but the initial torque for operating the propulsion device is increased, As it may cause interference between fluid and fixed wing.

When the power source having the same output is used as a reference based on the fact that the respective fixed vanes are successively installed up to the point where the projected area of the entire fixed vane 101 is firstly closed, if,

Depending on the fluid density, the propulsive force can be increased by reducing the cylinder length and the fixed blade moving angle, increasing the number of cylinder bores and fixed wing, increasing the number of rotations per minute,

 Depending on the density of the fluid, it is possible to increase the propulsive force by increasing the cylinder length and the fixed blade moving angle, reducing the number of the cylindrical bores and the number of fixed wings, and reducing the number of revolutions per minute,

As the cylinder diameter increases, the height of the fixed blade increases in proportion to the diameter of the cylinder. If the number of rotations is the same, the fluid flow rate and the amount of fluid movement per unit time can be increased. However,

When the length of the cylinder is increased, the length of the fixed blade is increased and the number of revolutions is increased, the fluid flow rate and the amount of fluid movement per unit time can be increased, but the weight of the rotor is increased,

The longer the distance that the projected area is firstly closed, the more the fluid flow rate can be increased, and the vibration of the cylinder 100 can be reduced, but the weight including the rotor and the fluid is heavily correlated .

Fig. 3 is a diagram illustrating an installation method and function of an iron plate for cylindrical displacement control, a steel plate for vibration control, and a rim gear for power transmission mounted on a cylinder, among the constituent devices of the rotor according to the present invention , The steel plate 103 for controlling displacement of the cylinder is used when the dimension of the outer section of the cylinder exceeds the maximum dimension of the displacement control bearing which is produced in general use and the direction of fluid flow of the cylinder caused by the contact between the fluid and the fixed blade In order to suppress the displacement occurring in the direction opposite to the direction of rotation, at least one or more fixedly installed on the outer surface of the cylinder,

The steel plate 104 for controlling the cylindrical vibration is used when the outer cross-sectional dimension of the cylinder exceeds the maximum dimension of the general-purpose produced vibration control bearing, and the vibration of the cylinder caused by the contact angle between the fluid and the fixed blade At least one or more fixedly installed on the outer surface of the cylinder,

The power transmitting rim gears 105 are connected to sprockets and shafts, and at least one of the rim gears 105 is fixed to the outer surface of the cylinder.

FIG. 4 is a view for schematically explaining a method of installing a vibration control device and a displacement control device among constituent devices of a rotor according to the present invention, in which at least one displacement control steel plate 103 is installed And the installation direction of the displacement control roller 106 will be described,

When the displacement control device is larger than the maximum allowable dimension of the displacement control bearing acting in the direction of the rotation axis in which the outer dimension of the cylinder is generally produced, three or more displacement control rollers 106 can be installed per one device In addition,

When the vibration control device is larger than the maximum allowable dimension of the vibration control bearing acting in the direction perpendicular to the rotation axis, in which the outer dimension of the cylinder is generally produced, at least two vibration control rollers 107 are provided per unit And,

Further, the cylindrical displacement control device and the vibration control device indicate that the support structure can be separately installed.

FIG. 5 is a schematic illustration of a device for constructing a rotor according to the present invention, which is a schematic illustration of a cylinder 100 supporting device and a method of installing the same, in which a cylindrical bearing outer diameter At least three support rollers 108 are provided at one location of the apparatus in accordance with the length of the cylinder and the direction of the rotation axis of the rollers is set parallel to the direction of the cylindrical rotation axis, Or more, and that the related supporting structures can be installed together.

6 is a diagram illustrating a method of installing a propulsion device for vertical take-off and landing and a predicted effect of the propulsion device for vertical takeoff and landing in a flight vehicle that obtains propulsion force using a jet engine or a gas turbine, And the other devices constituting the rotor, the cylinder diameter and length are appropriately adjusted according to the installation interval of the flight wing frame, the installation angle between the fixed blades is reduced, and the rotation speed per minute (rpm) Height is used,

In addition, it is possible to allow vertical takeoff and landing by installing propulsion devices 602 and 603 on both wings of the air vehicle 601,

Further, the propulsion devices 602 and 603 are arranged such that the rotational directions of the propulsion devices are opposite to each other,

Further, the propulsion devices 602 and 603 indicate that after the vertical take-off, the opening and closing device (not shown) provided on the wing of the air vehicle 601 can be hid in the wing.

Also, with this effect, the runway length required for taking off and landing the air vehicle 601 can be reduced,

Further, it shows that noise and air vibration phenomenon occurring during takeoff and landing of the air vehicle 601 can be reduced by the effect of the operation principle of the propulsion unit.

FIG. 7 is a diagram illustrating a method of installing a propulsion device and a predictive effect according to the present invention, in a helicopter, which is one of applications of the present invention. In the case of the vertical take-off propulsion devices 702 and 703, The cylinder diameter and the height of the fixed blade are increased, the angle between the cylinder length and the fixed blade is reduced, and the number of revolutions per minute of the cylinder is increased.

In the case of the moving propelling device 705, the cylinder diameter and the fixed blade height are reduced, the angle between the cylinder length and the fixed blade is increased to 60 degrees or more, and the number of revolutions per minute of the cylinder is increased ,

In addition, vertical landing and landing can be achieved by installing at least one vertical landing propulsion device 702, 703 on each of upper portions of the helicopter 701,

Further, the propulsion devices 702 and 703 are arranged such that the rotational directions of the propulsion devices are opposite to each other,

In addition, the propulsion unit 705 may be installed at least one position on both sides of the rear trunk of the helicopter for low-speed movement of the helicopter without using the propulsion device 704 for high-speed movement after the vertical take-off of the helicopter,

In addition, hovering can be easily performed by adjusting the rotational speed of the vertical take-off and landing propulsion device 702, 703 after the helicopter takes off vertically,

After the helicopter is vertically taken off, the propelling device 705 for low-speed movement, which is located opposite to the turning direction, is operated with respect to the center of the helicopter body while maintaining the rotational speed of the propelling devices 702 and 703 for vertical take- This makes it easy to turn the helicopter,

Also, it is shown that the effect of the operation principle of the propulsion device can reduce the noise and the vibration phenomenon of the air generated during the landing and landing of the helicopter 701.

FIG. 8 is a diagram illustrating a method of installing a propulsion device and a predicted effect according to the present invention, which is one of applications of the present invention. In FIG. 8, ) Is applied to the propulsion system,

At least one external rotor that is submerged in fluid may be installed in the ship stern 801,

In addition, the supporting frame 803 may be installed at least at one or more positions with a structure in which the shaft passes inside and the shaft is closed so as not to be in direct contact with the fluid,

The support frame 803 may be fixedly connected to the housing 102 and the ship stern 801,

Further, the supporting frame 803 can withstand the vibrations of the rotor generated according to the moving direction of the ship and the fluid flowing direction,

In addition, the supporting frame 804 can balance the rotor, and can catch the vibration of the rotor, which occurs according to the moving direction of the ship and the fluid flowing direction.

The support frame 804 can be fixedly connected to the housing 102 and the ship stern 801 at least at one or more positions,

In addition, one ship direction switching propulsion device 805 may be provided at the inner center of each duct 806 installed at least one place below the ship head 802 to facilitate the ship direction change ,

In addition, the duct 806 may be provided with a fluid shutoff device (not shown) that can block the inflow of fluid into the inlet and the outlet.

In addition, the fluid shut-off device installed on the front and rear surfaces of the duct 806 is operated to shut off fluid inflow, and the built-in propulsion device 805 can be refurbished inside the ship with the ship anchored to the water- ,

The propulsion device 805 is a method for changing the direction of rotation of the shaft connected to the propulsion device or installing two shafts on the propulsion device to operate one shaft applied in accordance with the direction of rotation. The direction of rotation of the ship can be changed and it is possible to change the direction of the ship in both directions even under half the number of conventional propulsion devices used for turning the ship.

100: Cylinder or casing model
101: Fixed wing model
102: housing model
103: Circular iron plate for cylinder displacement control
104: Triangular iron plate for cylindrical vibration control
105: Power transmission rim gear model
106: Cylinder Displacement Control Roller Model
107: Roller model for cylinder vibration control
108: Cylinder support roller model
109: Fluid Inlet Induction Device Model
110: Fluid flow induction device model
111: Structural wall model isolated from fluid
112: Internal model of fluid isolated structure
201: Location of a certain distance from the inlet of the cylinder to the inside of the cylinder
202: the position where the additional movement from the position 201 to the inside of the cylinder
203: Cylinder outlet
204: When the cylinder is cut in the longitudinal direction in the position 201, the displacement model of the fixed blade viewed from the cylindrical inlet
205: When the cylinder is cut in the longitudinal direction in the position 202, the displacement model of the fixed blade viewed from the cylindrical inlet
206: displacement model of the fixed blade in the cylindrical cross section from the inlet of the cylinder to the above-mentioned position (203)
601: Aircraft model driven by jet engine or gas turbine
602, 603: a propulsion device that rotates counter to each other for vertical take-off and landing
701: Helicopter model
702, 703: a propulsion device that rotates in opposite directions for vertical take-off and landing
704: Existing propulsion unit model for high-speed movement
705: Propulsion unit model for helicopter forward movement
801: Stern model of ship
802: Ship's head model
803: Shaft protection installed at the bottom of the ship's stern and supporting frame model fixedly connected with the propelling device housing
804: Supporting frame model fixedly connected to the propulsion unit housing installed at the bottom of ship's stern
805: Propulsion system for changing direction of ship installed inside duct
806: Duct model for fluid distribution installed at the bottom of ship head
M Oil: Mass of fluid flowing into the cylinder (kg)
V1: Fluid velocity entering the cylinder (m / sec)
V2: Fluid velocity out of the cylinder (m / sec)
R Oil: Rotation radius of the fluid flowing out of the cylinder (m)
W oil: Fluid rotation angular velocity (radian / sec)
Meter: Rotor mass including the cylinder (kg)
Rotor: Rotor rotation radius (m)
Rotor angular velocity (radian / sec)
FEtter: The energy (k × gm² / sec²) that causes vibration and displacement in the rotor due to the interaction between rotating cylinder and fixed vane and fluid.

Claims (31)

A rotor;
Guidance device;
housing;
A propulsion device comprising a rotor support frame. 2. The rotor of claim 1,
A fixed blade mounted inside the cylinder;
A power transmitting device for transmitting rotational force to the cylinder;
A displacement control device for controlling the cylindrical displacement;
A vibration control device for controlling the cylindrical vibration;
A support device for supporting the weight of the cylinder and the fluid and maintaining the rotation of the cylinder;
And a leakage prevention device installed at both end points of the cylinder. [2] The method of claim 1, wherein the rotor is installed in the housing at least at one or more locations in the fluid, and the rotor is installed in the housing inside the vessel, And at least one position can be installed by installing it in the interior of the aircraft. [5] The apparatus according to claim 1 or 3, wherein, when the rotor is installed inside the vessel, a fluid cutoff device capable of blocking fluid inflow can be installed on the front and rear surfaces of the inductive device, Wherein each of the accessory devices of the propulsion device can be easily maintained after shutting off the fluid inflow. The rotor support structure according to claim 1, wherein the rotor support frame is divided into a type in which the shaft passes inside and a shaft-free type in which the propulsion body and the housing are connected to each other. Wherein the rotor is installed at one or more positions, and has sufficient rigidity and durability to withstand the interference and vibration between the propellant and the fluid. 2. The apparatus according to claim 1, wherein at least one guide member for dispersing the fluid to be discharged or for reducing the fluid rotational force is installed inside or outside the induction device And the guide member can be formed in a straight line or a ring shape or a combination of a straight line and a ring. The displacement control device according to claim 2, wherein the cylindrical body is a pipe having a circular cross-section with an open end and an open end, and is provided with a rim gear for transmitting power, a displacement control device, And a water leakage preventing device are provided, and is rotated together with a fixed blade installed inside the cylinder. [3] The apparatus according to claim 2, wherein the stationary vanes are installed at least one inside the cylinder, and the fixed ends of the vanes are at an angle of 90 degrees with the inner surface of the cylinder, Are identical to each other, and each wing is continuously installed along the inner surface of the cylinder while maintaining the same displacement. 3. The propulsion device according to claim 2, wherein the fixed blade is installed to a position where at least a projected area of each blade is firstly closed, with respect to a cylindrical longitudinal cross section. The fixed blade according to claim 2, wherein the fixed blade is capable of increasing propulsion force by changing the angle formed by the center of the fixed end of the blade and the free end center on the inner surface of the cylinder with respect to the cross section in the longitudinal direction of the cylinder, Characterized by a propulsion device. 3. The method of claim 2, wherein the stationary vane is configured to minimize the turbulence of fluids occurring at the center of the cylindrical cross-section by making each wing height less than 50% of the cylinder bore with respect to the cross- Wherein the propulsion device is capable of increasing propulsion force. 3. The propulsion apparatus according to claim 2, wherein the power transmission device includes a power transmitting rim gear, a sprocket, and a shaft fixedly mounted on at least one outer surface of the cylinder. 3. The displacement control device according to claim 2, wherein the displacement control device is provided with a displacement control steel plate and three or more rollers in combination with a separate support device And the displacement of the cylinder is controlled by a method in which the cylinder is installed at an angle of 90 degrees with the cylinder rotary shaft and installed at least one place on the outer surface of the cylinder. The vibration control apparatus as claimed in claim 2, wherein the vibration control device comprises a vibration control steel plate fixed to the outer surface of the cylinder in the form of a triangular ring when two or more rollers Wherein the vibration of the cylinder is controlled by a method that is installed together with a separate supporting device in a combined form and installed at an angle of 90 degrees with the cylindrical rotary shaft and installed at least at one or more positions on the outer surface of the cylinder. [3] The apparatus according to claim 2, wherein the supporting device is installed together with a separate supporting device in a form of three or more rollers when the cylindrical outer dimension is large enough to prevent a supporting bearing produced as a general purpose from being installed, Wherein each of the roller rotating shafts is provided on the outer surface of the cylinder in a state in which the rotating shafts are parallel to each other and at least one position is provided so as to enable cylinder rotation while supporting the weight of the cylinder and the fluid. A process of increasing the propulsion efficiency of the propulsion device by rotating the cylinder and the fixed vane together along the cylinder rotational axis;
A process for increasing the propulsion efficiency of a propulsion device by installing a cylinder in a housing or inside a structure isolated from an external fluid;
A process for increasing the propulsion efficiency of the propulsion device by adjusting the cylinder diameter and length, the number and height of the fixed blades, the moving angle, and the installation length according to the maximum moving speed and fluid density to be expressed by the propellant;
The method of adjusting the bending angle from the center of the fixed end of the fixed wing to the center of the free end according to the maximum speed of movement and the density of fluid to be expressed by the propellant, ;
In a flight vehicle that obtains propulsive force by using a jet engine or a gas turbine, at least one propulsion device for vertical takeoff and landing is installed for each wing of the airplane to enable vertical takeoff and landing of the airplane;
In the helicopter, at least one propulsion device for vertical take-off and landing is installed on each side of the helicopter body so that vertical takeoff and landing of the helicopter is possible, and at least one horizontal propulsion device is installed on each side of the helicopter, A step of enabling movement;
A step of increasing the propulsion efficiency of the ship by installing at least one propulsion device in the lower part of the rear tail of the ship;
A propulsion method using a propulsion device including a step of increasing a direction conversion efficiency of a ship by installing a propulsion device for changing direction at a center of a duct for fluid distribution provided at a lower portion of a ship head. 17. The method of claim 16, wherein the step of increasing the propulsion efficiency of the propulsion device in such a way that the cylinder and the fixed vane rotate together along the cylindrical rotational axis,
As the cylinder and the fixed blade are integrally rotated by the rim gear mounted on the outer surface of the cylinder, the inner fluid of the cylinder and the outer fluid are disconnected from each other,
In addition, since the rotational center of the fluid inside the cylindrical longitudinal direction is located in the region between the free ends of the fixed blades and the center of the sectional plane, the turbulence intensity of the fluid generated at the free ends of the fixed blades becomes weak,
In addition, since the respective fixed vanes maintain the same moving form along the inner surface of the cylinder and rotate, the flow velocity of the fluid expressed in all the cylinders provided with the fixed vanes is formed to be the same size, Wherein the propulsion system is a propulsion system. 17. The method of claim 16, wherein the step of increasing the propulsion efficiency of the propulsion device by installing the cylinder inside the housing or inside the structure isolated from the external fluid includes rotating the cylinder inside the housing, Thereby reducing the turbulence of the external fluid due to the operation of the rotor,
Wherein the propulsion efficiency of the propulsion device is enhanced by reducing the transfer of energy transferred to the fluid inside the cylinder through the rotor to the external fluid. The method according to claim 16, wherein the propulsion efficiency of the propulsion device is increased by adjusting the diameter and length of the cylinder, the number and height of the fixed blades, the moving angle, and the installation length according to the maximum moving speed and fluid density desired to be expressed by the propellant Is a method for increasing the thrust of the propulsion device, which limits the height of the fixed wing to less than 50% of the bore diameter,
In addition, the angles between the wings at the longitudinal cross-sectional center of the cylinder are made the same,
In addition, the number and height of the fixed blades are increased in proportion to the diameter of the cylinder,
Further, the propulsion efficiency of the propulsion device is enhanced by using various methods such as adjusting the installation length of the fixed blade up to the point where the projected area of the entire blade is firstly closed in inverse proportion to the diameter of the cylinder Way. 20. The method according to claim 19, wherein adjusting the fixed wing installation length up to the point where the entire wing projected area is first closed is performed by taking into account the self weight of the rotor, the installation method, the weight of the propellant, Wherein the propulsion efficiency of the propulsion device including the step of deriving the fixed blade installation length that can be maximally expressed is enhanced. The method according to claim 16, further comprising the step of adjusting the bending angle from the center of the fixed end of the stationary vane to the center of the free end according to the maximum movement speed and fluid density of the propellant to be expressed , The process of increasing the propulsion efficiency of the propulsion device is a process in which the free end of the fixed blade at an arbitrary cross section in the longitudinal direction of the cylinder contacts the line connecting the fixed end center of the fixed blade and the center of the cylindrical cross section, Bending circularly in the direction of the wing contact surface,
The propulsion method using a propulsion device according to claim 1, wherein the propulsion efficiency of the propulsion device is enhanced by using the effect of increasing the contact angle with the fluid and expanding the contact area, which is represented by a method of raising the blade height by a reduced height. 17. The method according to claim 16, wherein, in a flight vehicle that obtains propulsive force using a jet engine or a gas turbine, at least one propulsion device for vertical takeoff and landing is installed for each wing of the flight vehicle to enable vertical takeoff and landing of the flight vehicle, A step of installing at least one propelling device for vertical takeoff and landing on the wing and keeping the direction of rotation of each propelling device opposite;
It is necessary to adjust the cylindrical diameter of the rotor and the height of the fixed blade to suit the flight wing frame to reduce the angle between the cylinder length and the fixed blade and to increase the number of revolutions per minute of the cylinder, Forming an air reaction force;
A step of variably adjusting the revolution speed per minute of each vertical take-off propulsion device to the same value;
And a high speed traveling operation using a jet engine by operating an opening / closing device installed on a flight wing after vertical takeoff of a flight vehicle to incorporate a vertical takeoff and landing propulsion device into a wing. 23. The method according to claim 22, wherein at least one propulsion device for vertical takeoff and landing is installed at each wing of the flight vehicle and the direction of rotation of each propulsion device is reversed by reversing the direction of rotation of each propulsion device installed on both wings of the flight vehicle, Wherein the balance of the air vehicle for taking off or landing vertically can be easily maintained. 23. The method of claim 22, further comprising the step of adjusting the cylindrical diameter of the rotor and the height of the fixed vanes to suit the flight vane frame to reduce the angle between the cylinder length and the fixed vanes, The process of forming sufficient air reaction force for takeoff and landing of the airplane is to adjust the cylinder clearance to less than the inner space thickness of the flight wing and to adjust the diameter of the cylinder to a size that can be located between the inner flight wings, Increasing the number of blades by reducing the angle between the fixed blades and maintaining the balance when the propulsion unit is operated by installing two power transmission units per propulsion unit and increasing the number of revolutions per minute of the cylinder Is used as the propulsion device. 23. The method according to claim 22, wherein the step of varying the rotational speed per minute of each propelling device for vertical take-off and landing is the same as the method of operating a lever capable of adjusting the number of revolutions per minute of the propelling device Wherein the number of revolutions per minute of each propulsion device can be variably adjusted to be the same, and as a result, hovering of the air vehicle can be easily performed. 23. The method according to claim 22, wherein, after the vertical take-off of the airplane, the open / close device installed on the airplane wing is operated to embed the propulsion device for vertical takeoff and landing into the wing, In order to eliminate the interaction between air and the vertical takeoff and landing propulsion device during high speed flight by attaching the device inside the flight wing and disconnecting the propulsion device for vertical takeoff and landing from the outside of the wing by operating the opening and closing device, Wherein the propulsion device is capable of traveling. The helicopter as set forth in claim 16, wherein at least one vertical propulsion device for vertical takeoff and landing is installed at each of at least one helicopter body to enable vertical takeoff and landing of the helicopter, The helicopter can be moved horizontally by installing at least one propulsion device for vertical takeoff and landing which is opposite in direction of rotation on both sides of the helicopter body to reduce noise and air vibration generated in a conventional helicopter, Wherein when the low speed flight is required, the propelling efficiency of the propulsion device is increased by operating the horizontal movement propulsion device installed on both sides of the rear body of the helicopter to reduce fuel consumption. The method of claim 27, further comprising the steps of: hovering by adjusting the rotational speed of the vertical take-off and landing propulsion device while the horizontal movement propulsion device is stopped; Wherein the propulsion device is driven by a horizontal movement propulsion device installed on the opposite side to the helicopter, so that the helicopter hovering and turning can be easily performed, and the propulsion efficiency of the propulsion device is improved by reducing fuel consumption. How to use it. The process according to claim 16, wherein the step of increasing the propulsion efficiency of the ship by installing at least one propulsion device on the lower part of the rear tail of the ship is characterized in that at least one external rotor And a rotor support frame and a support frame separately connected to the ship and the housing are installed so as to catch the vibration of the rotor caused by the change of the moving direction of the ship and the fluctuation of the fluid flow direction, wherein the propulsion efficiency of the propulsion device is enhanced by balancing the rotor of the propulsion device. 17. The ship according to claim 16, wherein the step of increasing the direction conversion efficiency of the ship by installing a direction switching propulsion device in the center of the duct for fluid distribution provided at the lower part of the ship head is performed by connecting the propulsion device installed in the center of the duct Directional rotation of the propulsion device for direction is enabled by changing the rotation direction of the shaft to be rotated or by installing two shafts in the propulsion device and operating one shaft to be applied in accordance with the rotation direction, Compared with the existing type of thruster which is installed one by one, it is possible to reduce the number of the propulsion devices for turning direction by half or less,
A propulsion method using a propulsion device characterized in that propulsion efficiency of a propulsion device is enhanced by a method in which no interference with other propulsion device is generated during operation of the propulsion device by installing only one propulsion device in one duct. 31. The method as claimed in claim 30, wherein, when the direction switching propulsion device is refurbished, the fluid shut-off device installed on the front and rear surfaces of the duct is operated to shut off fluid inflow, So that the time and cost to be supplied to the repair work can be reduced.

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